Copyright: V0.34.001-158 for Radio Club Bariloche
Citation: Copyright ® 1993-1996 Tag's Broadcasting Services


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Main index
 The Satellite's Encyclopedia

By Jean-Philippe Donnio with the help of Jean-Jacques Serra, Gunter Krebs and numerous other contributors.

Country of origin	Mission	Glossary
Launch vehicle	The Clarke Belt	To be launched

Alphabetical satellite index

Help: how to use this encyclopedia?

Designation numbers

First in History

EIRP maps


 Alphabetical satellite index

A

ACTS

AEM 1

AEM 2

AEM 3

Program: Aeros

Aeros 1

Aeros 2

Ajisai

Alexis

Program: Alouette

Alouette 1

Alouette 2

Program: AMPTE

AMPTE CCE

AMPTE IRM

AMPTE UKS

Program: AMS

Program: AMSC

AMSC 1

Program: Anik

Anik A1

Anik A2

Anik A3

Anik B1

Anik C1

Anik C2

Anik C3

Anik D1

Anik D2

Anik E1

Anik E2

Anna 1B

ANS

Apex

Apple

Program: Apstar

Apstar 1

Apstar 2

Program: Arabsat

Arabsat 1A

Arabsat 1B

Arabsat 1C

Arabsat 1D

Arabsat 1E

Program: Argos

Program: Ariel

Ariel 1

Ariel 2

Ariel 3

Ariel 4

Ariel 5

Ariel 6

Arsène

Aryabhata

Program: ASC

ASC 1

ASC 2

Program: Asiasat

Asiasat 1

Asiasat 2

Astérix

Program: Astra

Astra 1A

Astra 1B

Astra 1C

Astra 1D

Astra 1E

Astrid

Program: Astro

Astro A

Astro B

Astro C

Astro D

Astron

Program: ATS

ATS 1

ATS 3

ATS 5

ATS 6

Aura

Program: Auréole

Auréole 1

Auréole 2

Auréole 3

Program: Aurora

Aurora 1

Aurora 2

Program: Ayame

Ayame 1

Ayame 2

Azur

B

Badr A

Program: Bhaskara

Bhaskara 1

Bhaskara 2

Program: Brazilsat

Brazilsat A1

Brazilsat A2

Brazilsat B1

Brazilsat B2

Bremsat

Program: BSB

BSB 1

BSB 2

C

Castor

Program: Cat

Cat 1

Cat 2

Cat 3

Cat 4

Cerise

COBE

Program: Comstar

Comstar 1

Comstar 2

Comstar 3

Comstar 4

Corsa B

Cos B

Program: Cosmos

Cosmos 0001

Cosmos 0100

Cosmos 0110

Cosmos 0122

Cosmos 0144

Cosmos 0169

Cosmos 0186

Cosmos 0188

Cosmos 0368

Cosmos 0444

Cosmos 0445

Cosmos 0446

Cosmos 0447

Cosmos 0448

Cosmos 0449

Cosmos 0450

Cosmos 0451

Cosmos 0500

Cosmos 0504

Cosmos 0505

Cosmos 0506

Cosmos 0507

Cosmos 0508

Cosmos 0509

Cosmos 0510

Cosmos 0511

Cosmos 0588

Cosmos 0589

Cosmos 0590

Cosmos 0591

Cosmos 0592

Cosmos 0593

Cosmos 0594

Cosmos 0595

Cosmos 0596

Cosmos 0597

Cosmos 0598

Cosmos 0599

Cosmos 0600

Cosmos 0605

Cosmos 0637

Cosmos 0641

Cosmos 0642

Cosmos 0643

Cosmos 0644

Cosmos 0645

Cosmos 0646

Cosmos 0647

Cosmos 0648

Cosmos 0677

Cosmos 0678

Cosmos 0679

Cosmos 0680

Cosmos 0681

Cosmos 0682

Cosmos 0683

Cosmos 0684

Cosmos 0711

Cosmos 0712

Cosmos 0713

Cosmos 0714

Cosmos 0715

Cosmos 0716

Cosmos 0717

Cosmos 0718

Cosmos 0732

Cosmos 0733

Cosmos 0734

Cosmos 0735

Cosmos 0736

Cosmos 0737

Cosmos 0738

Cosmos 0739

Cosmos 0775

Cosmos 0777

Cosmos 0782

Cosmos 0936

Cosmos 0954

Cosmos 1000

Cosmos 1094

Cosmos 1267

Cosmos 1366

Cosmos 1402

Cosmos 1443

Cosmos 1540

Cosmos 1546

Cosmos 1629

Cosmos 1700

Cosmos 1738

Cosmos 1849

Cosmos 1850

Cosmos 1851

Cosmos 1852

Cosmos 1853

Cosmos 1854

Cosmos 1855

Cosmos 1856

Cosmos 1857

Cosmos 1858

Cosmos 1859

Cosmos 1860

Cosmos 1861

Cosmos 1870

Cosmos 1887

Cosmos 1888

Cosmos 1894

Cosmos 1897

Cosmos 1923

Cosmos 1924

Cosmos 1925

Cosmos 1926

Cosmos 1927

Cosmos 1928

Cosmos 1929

Cosmos 1930

Cosmos 1931

Cosmos 1932

Cosmos 1933

Cosmos 1934

Cosmos 1935

Cosmos 1957

Cosmos 1958

Cosmos 1959

Cosmos 1960

Cosmos 1961

Cosmos 1962

Cosmos 1963

Cosmos 1964

Cosmos 1965

Cosmos 1966

Cosmos 1967

Cosmos 1968

Cosmos 1969

Cosmos 1970

Cosmos 1971

Cosmos 1972

Cosmos 1973

Cosmos 1974

Cosmos 1975

Cosmos 1976

Cosmos 1977

Cosmos 1978

Cosmos 1979

Cosmos 1980

Cosmos 1982

Cosmos 1983

Cosmos 1984

Cosmos 1985

Cosmos 1986

Cosmos 1987

Cosmos 1988

Cosmos 1989

Cosmos 1990

Cosmos 1991

Cosmos 1992

Cosmos 1993

Cosmos 1994

Cosmos 1995

Cosmos 1996

Cosmos 1997

Cosmos 1998

Cosmos 1999

Cosmos 2000

Cosmos 2001

Cosmos 2002

Cosmos 2003

Cosmos 2004

Cosmos 2005

Cosmos 2006

Cosmos 2007

Cosmos 2008

Cosmos 2009

Cosmos 2010

Cosmos 2011

Cosmos 2012

Cosmos 2013

Cosmos 2014

Cosmos 2015

Cosmos 2016

Cosmos 2017

Cosmos 2018

Cosmos 2019

Cosmos 2020

Cosmos 2021

Cosmos 2022

Cosmos 2023

Cosmos 2024

Cosmos 2025

Cosmos 2026

Cosmos 2027

Cosmos 2028

Cosmos 2029

Cosmos 2030

Cosmos 2031

Cosmos 2032

Cosmos 2033

Cosmos 2034

Cosmos 2035

Cosmos 2036

Cosmos 2037

Cosmos 2038

Cosmos 2039

Cosmos 2040

Cosmos 2041

Cosmos 2042

Cosmos 2043

Cosmos 2044

Cosmos 2045

Cosmos 2047

Cosmos 2048

Cosmos 2049

Cosmos 2050

Cosmos 2051

Cosmos 2052

Cosmos 2054

Cosmos 2055

Cosmos 2056

Cosmos 2057

Cosmos 2058

Cosmos 2059

Cosmos 2061

Cosmos 2062

Cosmos 2063

Cosmos 2064

Cosmos 2065

Cosmos 2066

Cosmos 2067

Cosmos 2068

Cosmos 2069

Cosmos 2070

Cosmos 2071

Cosmos 2072

Cosmos 2073

Cosmos 2074

Cosmos 2079

Cosmos 2080

Cosmos 2081

Cosmos 2085

Cosmos 2100

Cosmos 2107

Cosmos 2108

Cosmos 2109

Cosmos 2110

Cosmos 2111

Cosmos 2112

Cosmos 2123

Cosmos 2133

Cosmos 2139

Cosmos 2140

Cosmos 2141

Cosmos 2142

Cosmos 2172

Cosmos 2173

Cosmos 2177

Cosmos 2178

Cosmos 2179

Cosmos 2204

Cosmos 2205

Cosmos 2206

Cosmos 2209

Cosmos 2218

Cosmos 2219

Cosmos 2220

Cosmos 2221

Cosmos 2222

Cosmos 2223

Cosmos 2224

Cosmos 2230

Cosmos 2231

Cosmos 2232

Cosmos 2233

Cosmos 2234

Cosmos 2235

Cosmos 2236

Cosmos 2237

Cosmos 2238

Cosmos 2239

Cosmos 2240

Cosmos 2241

Cosmos 2242

Cosmos 2243

Cosmos 2244

Cosmos 2245

Cosmos 2246

Cosmos 2247

Cosmos 2248

Cosmos 2249

Cosmos 2250

Cosmos 2251

Cosmos 2252

Cosmos 2253

Cosmos 2254

Cosmos 2255

Cosmos 2256

Cosmos 2257

Cosmos 2258

Cosmos 2259

Cosmos 2260

Cosmos 2261

Cosmos 2262

Cosmos 2263

Cosmos 2264

Cosmos 2265

Cosmos 2266

Cosmos 2267

Cosmos 2268

Cosmos 2269

Cosmos 2270

Cosmos 2271

Cosmos 2272

Cosmos 2273

Cosmos 2274

Cosmos 2275

Cosmos 2276

Cosmos 2277

Cosmos 2278

Cosmos 2279

Cosmos 2280

Cosmos 2281

Cosmos 2282

Cosmos 2283

Cosmos 2284

Cosmos 2285

Cosmos 2286

Cosmos 2287

Cosmos 2288

Cosmos 2289

Cosmos 2290

Cosmos 2291

Cosmos 2292

Cosmos 2293

Cosmos 2294

Cosmos 2295

Cosmos 2296

Cosmos 2297

Cosmos 2298

Cosmos 2299

Cosmos 2300

Cosmos 2301

Cosmos 2302

Cosmos 2303

Cosmos 2304

Cosmos 2305

Cosmos 2306

Cosmos 2307

Cosmos 2308

Cosmos 2309

Cosmos 2310

Cosmos 2311

Cosmos 2312

Cosmos 2313

Cosmos 2314

Cosmos 2315

Cosmos 2316

Cosmos 2317

Cosmos 2318

Cosmos 2319

Cosmos 2320

Cosmos 2321

Cosmos 2322

Cosmos 2323

Cosmos 2324

Cosmos 2325

Cosmos 2326

Cosmos 2327

Cosmos 2328

Cosmos 2329

Cosmos 2330

Cosmos 2331

Courier 1B

CTA

CTS

D

Program: Dash

Program: DBS

DBS 1

DBS 2

DBS 3

Delta

Denpa

Program: DFS Kopernikus

DFS 1

DFS 2

DFS 3

Program: Diadème

Diadème 1

Diadème 2

Dial-Wika

Diapason

Program: Discoverer

Program: DMSP

DMSP B5D2-3

DMSP B5D2-7

DMSP B5D2-8

Program: Dong Fang Hong

Dong Fang Hong 01

Dong Fang Hong 02

Dong Fang Hong 03

Dong Fang Hong 04

Dong Fang Hong 05

Dong Fang Hong 06

Dong Fang Hong 07

Dong Fang Hong 08

Dong Fang Hong 09

Dong Fang Hong 10

Dong Fang Hong 11

Dong Fang Hong 12

Dong Fang Hong 13

Dong Fang Hong 14

Dong Fang Hong 15

Dong Fang Hong 16

Dong Fang Hong 17

Dong Fang Hong 18

Dong Fang Hong 19

Dong Fang Hong 20

Dong Fang Hong 21

Dong Fang Hong 22

Dong Fang Hong 23

Dong Fang Hong 24

Dong Fang Hong 25

Dong Fang Hong 26

Dong Fang Hong 30

Dong Fang Hong 31

Dong Fang Hong 32

Dong Fang Hong 33

Dong Fang Hong 34

Dong Fang Hong 35

Dong Fang Hong 36

Dong Fang Hong 37

Dong Fang Hong 38

Dong Fang Hong 39

Dong Fang Hong 40

Dong Fang Hong 41

Dove

Program: DSCS

DSCS 2-01

DSCS 2-02

DSCS 2-03

DSCS 2-04

DSCS 2-05

DSCS 2-06

DSCS 2-07

DSCS 2-08

DSCS 2-11

DSCS 2-12

DSCS 2-13

DSCS 2-14

DSCS 2-15

DSCS 2-16

DSCS 3-01

DSCS 3-02

DSCS 3-03

DSCS 3-04

DSCS 3-05

DSCS 3-06

DSCS 3-07

DSCS 3-08

DSCS 3-09

Program: DSP

DSP F12

DSP F13

DSP F14

DSP F15

DSP 3-4

DSP 3-5

Dynamics Explorer 1

Dynamics Explorer 2

E

Program: Echo

Echo 1

Echo 2

Program: Echostar

Echostar 1

Program: Ekran

Ekran 01

Ekran 02

Ekran 03

Ekran 04

Ekran 05

Ekran 06

Ekran 07

Ekran 08

Ekran 09

Ekran 10

Ekran 11

Ekran 12

Ekran 13

Ekran 14

Ekran 15

Ekran 16

Ekran 17

Ekran 18

Ekran 19

Ekran 20

Electro 1

Program: Elektron

Elektron 1

Elektron 2

Elektron 3

Elektron 4

Eole

Program: Eorsat

ERBS

Program: ERS

ERS 1

ERS 2

ESA-Geos 1

ESA-Geos 2

Program: Esro

Esro 1A

Esro 1B

Esro 2B

Esro 4

Program: Essa

Essa 1

Essa 2

Essa 3

Essa 4

Essa 5

Essa 6

Essa 7

Essa 8

Essa 9

Program: ETS

ETS 1

ETS 2

ETS 3

ETS 4

ETS 5

ETS 6

Eureca 1

Program: Eutelsat

Eutelsat 1F1

Eutelsat 1F2

Eutelsat 1F3

Eutelsat 1F4

Eutelsat 1F5

Eutelsat 2F1

Eutelsat 2F2

Eutelsat 2F3

Eutelsat 2F4

Eutelsat 2F5

EUVE

Program: Exos

Exos A

Exos B

Exos C

Exos D

Exosat

Program: Explorer

Explorer 01

Explorer 03

Explorer 04

Explorer 06

Explorer 07

Explorer 08

Explorer 09

Explorer 10

Explorer 11

Explorer 12

Explorer 13

Explorer 14

Explorer 15

Explorer 16

Explorer 17

Explorer 18

Explorer 19

Explorer 20

Explorer 21

Explorer 22

Explorer 23

Explorer 24

Explorer 25

Explorer 26

Explorer 27

Explorer 28

Explorer 29

Explorer 30

Explorer 31

Explorer 32

Explorer 33

Explorer 34

Explorer 36

Explorer 38

Explorer 39

Explorer 40

Explorer 41

Explorer 42

Explorer 43

Explorer 45

Explorer 46

Explorer 47

Explorer 48

Explorer 50

Explorer 51

Explorer 52

Explorer 53

Explorer 54

Explorer 55

EXPRESS (German)

Program: Express

Express 01

Eyesat

F

Program: Fasat

Fasat Alfa

Faisat

Firewheel

Program: Fleetsatcom

Fleetsatcom 1

Fleetsatcom 2

Fleetsatcom 3

Fleetsatcom 4

Fleetsatcom 5

Fleetsatcom 6

Fleetsatcom 7

Fleetsatcom 8

Program: Foton

Foton 09

Foton 10

FR 1

Freja

Program: Fuji

Fuji 1A

Fuji 1B

G

Program: Galaxy

Galaxy 1

Galaxy 1R

Galaxy 1R failure

Galaxy 2

Galaxy 3

Galaxy 3R

Galaxy 4

Galaxy 5

Galaxy 6

Galaxy 7

Program: Gals

Gals 1

Gals 2

Gamma

Program: Geizer

Gemstar

GEO-IK

Geos 3

Geotail

GFZ 1

Program: GGSE

GGSE 1

GGSE 2

GGSE 3

GGSE 4

GGSE 5

Program: Glonass

Program: GMS

GMS 1

GMS 2

GMS 3

GMS 4

GMS 5

Program: Goes

Goes 1

Goes 2

Goes 3

Goes 4

Goes 5

Goes 6

Goes 7

Goes 8

Goes 9

Program: Gorizont

Gorizont 01

Gorizont 02

Gorizont 03

Gorizont 04

Gorizont 05

Gorizont 06

Gorizont 07

Gorizont 08

Gorizont 09

Gorizont 10

Gorizont 11

Gorizont 12

Gorizont 13

Gorizont 14

Gorizont 15

Gorizont 16

Gorizont 17

Gorizont 18

Gorizont 19

Gorizont 20

Gorizont 21

Gorizont 22

Gorizont 23

Gorizont 24

Gorizont 25

Gorizont 26

Gorizont 27

Gorizont 28

Gorizont 29

Gorizont 30

Gorizont 31

Program: GPS

GPS BI-01

GPS BI-02

GPS BI-03

GPS BI-04

GPS BI-05

GPS BI-06

GPS BI-07

GPS BI-08

GPS BI-09

GPS BI-10

GPS BI-11

GPS BII-01

GPS BII-02

GPS BII-03

GPS BII-04

GPS BII-05

GPS BII-06

GPS BII-07

GPS BII-08

GPS BIIA-10

GPS BIIA-11

GPS BIIA-12

GPS BIIA-13

GPS BIIA-14

GPS BIIA-15

GPS BIIA-16

GPS BIIA-17

GPS BIIA-18

GPS BIIA-19

GPS BIIA-20

GPS BIIA-21

GPS BIIA-22

GPS BIIA-23

GPS BIIA-24

GPS BIIA-25

Granat

GRO

Program: Gstar

Gstar 1

Gstar 2

Gstar 3

Gstar 4

Gurwin 1

H

Healthsat

Program: Hélios

Hélios 1A

Program: Heoa

Heao 1

Heao 2

Heao 3

Program: Heos

Heos 1

Heos 2

Hipparcos

Program: Hispasat

Hispasat 1A

Hispasat 1B

Hotbird 1

HST

I

Program: IDSCP

Program: IMEWS

Informator

Injun 3

Program: Inmarsat

Inmarsat 2F1

Inmarsat 2F2

Inmarsat 2F3

Inmarsat 2F4

Program: Insat

Insat 1A

Insat 1B

Insat 1C

Insat 1D

Insat 2A

Insat 2B

Insat 2C

Intasat

Program: Intelsat

Intelsat 101

Intelsat 201

Intelsat 202

Intelsat 203

Intelsat 204

Intelsat 301

Intelsat 302

Intelsat 303

Intelsat 304

Intelsat 305

Intelsat 306

Intelsat 307

Intelsat 308

Intelsat 401

Intelsat 402

Intelsat 403

Intelsat 404

Intelsat 405

Intelsat 406

Intelsat 407

Intelsat 408

Intelsat 4A01

Intelsat 4A02

Intelsat 4A03

Intelsat 4A04

Intelsat 4A05

Intelsat 4A06

Intelsat 501

Intelsat 502

Intelsat 503

Intelsat 504

Intelsat 505

Intelsat 506

Intelsat 507

Intelsat 508

Intelsat 509

Intelsat 510

Intelsat 511

Intelsat 512

Intelsat 513

Intelsat 514

Intelsat 515

Intelsat 601

Intelsat 602

Intelsat 603

Intelsat 604

Intelsat 605

Intelsat 701

Intelsat 702

Intelsat 703

Intelsat 704

Intelsat 705

Intelsat 706

Intelsat 707

Intelsat 708

Intelsat K

Program: Intercosmos

Intercosmos 01

Intercosmos 18

Intercosmos Bulgaria 1300

Program: Intersputnik

IRAS

Program: IRS

IRS 1A

IRS 1B

IRS 1C

IRS 1E

IRS P2

IRS P3

IRT

Program: ISEE

ISEE 1

ISEE 2

Program: Isis

Isis 1

Isis 2

ISO

Program: Italsat

Italsat 1

Itamsat

Itos

IUE

J

Program: Jcsat

Jcsat 1

Jcsat 2

Jcsat 3

JERS 1

K

Program: KH

KH 1-2

KH 1-5

KH 4-01

KH 4A-03

KH 7-01

KH 9-01

KH 11-1

KH 11-2

KH 11-3

KH 11-6

KH 12-1

KH 12-2

KH 12-3

Program: Kitsat

Kitsat A

Kitsat B

Program: Koreasat

Koreasat 1

Koreasat 2

Koronas 1

L

Program: Lacrosse

Program: Lageos

Lageos 1

Lageos 2

Program: Landsat

Landsat 1

Landsat 2

Landsat 3

Landsat 4

Landsat 5

Landsat 6

Program: LCS

LCS 1

LCS 4

LDEF

Program: Leasat

Leasat 1

Leasat 2

Leasat 3

Leasat 4

Leasat 5

Program: LES

LES 1

LES 2

LES 3

LES 4

LES 5

LES 6

LES 8

LES 9

Program: Luch

Luch 0

Luch 1

Lusat

M

Program: Magion

Magion 1

Magion 2

Magion 3

Magion 4

Program: Marecs

Marecs A

Marecs B1

Marecs B2

Program: Marisat

Marisat 1

Marisat 2

Marisat 3

Program: Measat

Measat 1

Meteor (US)

Program: Meteor

Meteor 1-01

Meteor 1-02

Meteor 2-01

Meteor 2-21

Meteor 3-03

Meteor 3-05

Meteor 3-06

Program: Meteosat

Meteosat 1

Meteosat 2

Meteosat 3

Meteosat 4

Meteosat 5

Meteosat 6

Microlab 1

Program: Midas

Midas 02

Midas 03

Midas 04

Midas 05

Midas 06

Midas 07

Midas 08

Midas 09

Midas 10

Miranda

Program: Molniya

Molniya 1-01

Molniya 1-71

Molniya 1-72

Molniya 1-74

Molniya 1-85

Molniya 1-86

Molniya 1-87

Molniya 1-88

Molniya 2-01

Molniya 3-01

Molniya 3-34

Molniya 3-35

Molniya 3-36

Molniya 3-37

Molniya 3-42

Molniya 3-44

Molniya 3-45

Molniya 3-46

Molniya 3-47

Molniya 1-S

Program: Momo

Momo 1A

Momo 1B

Program: Morelos

Morelos 1

Morelos 2

MSTI 1

MSTI 2

Myojo

N

Program: N Star

N Star A

N Star B

Program: Nadezhda

Nadezhda 1

Nadezhda 2

Nadezhda 3

Nadezhda 4

Program: NATO

Nato 1

Nato 2

Nato 3A

Nato 3B

Nato 3C

Nato 3D

Nato 4A

Nato 4B

Program: Nimbus

Nimbus 1

Nimbus 2

Nimbus 3

Nimbus 3A

Nimbus 4

Nimbus 5

Nimbus 6

Nimbus 7

Program: NOAA

NOAA 01

NOAA 02

NOAA 03

NOAA 04

NOAA 05

NOAA 06

NOAA 07

NOAA 08

NOAA 09

NOAA 10

NOAA 11

NOAA 12

NOAA 13

NOAA 14

NOAA B

Program: NOSS

NOSS 01

NOSS 02

NOSS 03

NOSS 04

NOSS 05

NOSS 06

NOSS 07

NOSS 08

NOSS 09

NOSS 12

NOSS 13

Program: Nova

Nova 1

Nova 2

Nova 3

Program: N Star

N Star A

O

Program: OAO

OAO 1

OAO 2

OAO 3

OAO B

Program: Oderacs

Oderacs 1A

Oderacs 1B

Oderacs 1C

Oderacs 1D

Oderacs 1E

Oderacs 1F

Oderacs 2A

Oderacs 2B

Oderacs 2C

Oderacs 2D

Oderacs 2E

Oderacs 2F

Program: Offek

Offek 1

Offek 2

Offek 3

OFO

Program: OGO

OGO 1

OGO 2

OGO 3

OGO 4

OGO 5

OGO 6

Ohsumi

Program: Ocean

Ocean 1

Ocean 2

Ocean 3

Ocean 4

Olympus

Program: Optus

Optus A1

Optus A2

Optus A3

Optus B1

Optus B2

Optus B3

Program: Orbcomm

Orbcomm X

Orbcomm XP 1

Orbcomm FM 1

Orbcomm FM 2

Program: Orion

Orion 1

Program: Oscar

Oscar 01

Oscar 02

Oscar 03

Oscar 04

Oscar 05

Oscar 06

Oscar 07

Oscar 08

Oscar 09 failure

Oscar 10

Oscar 13

Program: OSO

OSO 1

OSO 2

OSO 3

OSO 4

OSO 5

OSO 6

OSO 7

OSO 8

Program: OTS

OTS 1

OTS 2

Program: OV

OV 1-02

OV 1-04

OV 1-05

OV 1-08

OV 1-09

OV 1-10

OV 1-13

OV 1-14

OV 1-19

OV 1-21

OV 2-1

OV 2-3

OV 2-5

OV 3-1

OV 3-2

OV 3-3

OV 3-4

OV 5-5

OV 5-6

OV 5-9

P

Pacsat

Pageos

Program: Palapa

Palapa A1

Palapa A2

Palapa B1

Palapa B2

Palapa B2P

Palapa B2R

Palapa B4

Palapa C1

Program: Panamsat

Panamsat 1

Panamsat 2

Panamsat 3

Panamsat 3R

Panamsat 4

Program: Pegasus

Pegasus 1

Pegasus 2

Pegasus 3

Pegsat

Péole

PMG

Polaire

Polar

Pollux

Posat

Program: Prognoz

Prognoz 01

Prognoz 02

Prognoz 03

Prognoz 04

Prognoz 05

Prognoz 06

Prognoz 07

Prognoz 08

Prognoz 09

Prognoz 10

Prognoz 11

Prospero

Program: Proton

Proton 1

Proton 2

Proton 3

Proton 4

R

Radarsat

Radcal

Program: Raduga

Raduga 01

Raduga 02

Raduga 03

Raduga 04

Raduga 05

Raduga 06

Raduga 07

Raduga 08

Raduga 09

Raduga 1-1

Raduga 1-2

Raduga 1-3

Raduga 10

Raduga 11

Raduga 12

Raduga 13

Raduga 14

Raduga 15

Raduga 16

Raduga 17

Raduga 18

Raduga 19

Raduga 20

Raduga 21

Raduga 22

Raduga 23

Raduga 24

Raduga 25

Raduga 26

Raduga 27

Raduga 28

Raduga 29

Raduga 30

Raduga 31

Raduga 32

Raduga 33

Program: Relay

Relay 1

Relay 2

Program: Resurs

Resurs F01

Resurs F02

Resurs F03

Resurs F04

Resurs F05

Resurs F06

Resurs F07

Resurs F08

Resurs F09

Resurs F10

Resurs F11

Resurs F12

Resurs F13

Resurs F14

Resurs F15

Resurs F16

Resurs F17

Resurs F18

Resurs F19

Resurs F20

Resurs 500

Resurs O1-3

REX 2

Program: Rohini

Rohini 1B

Rohini 2

Rohini 3

Program: Eorsat

Rosat

RS 15

Ryusei

S

S80T

Program: Safir

Program: Sakura

Sakura 1

Sakura 2A

Sakura 2B

Sakura 3A

Sakura 3B

Program: San Marco

San Marco 1

San Marco 2

San Marco 3

San Marco 4

San Marco 5

Sara

Program: Sarsat

Program: Satcom

Satcom 1

Satcom 1R

Satcom 2

Satcom 2R

Satcom 3

Satcom 3R

Satcom 4

Satcom C1

Satcom C3

Satcom C4

Satcom K1

Satcom K2

Program: SBS

SBS 1

SBS 2

SBS 3

SBS 4

SBS 5

SBS 6

SCD

Score

Seasat

Program: Secor

Secor 01B

Secor 02

Secor 03

Secor 04

Secor 05

Secor 06

Secor 07

Secor 08

Secor 09

Secor 13

Seds 1

Seds 2

SFU

Shinsei

Sich 1

Signe 3

Program: Sirio

Sirio 1

Sirio 2

Sirius 1

Program: Skynet

Skynet 1A

Skynet 1B

Skynet 2A

Skynet 2B

Skynet 4A

Skynet 4B

Skynet 4C

SME

SMM

Program: SMS

SMS 1

SMS 2

Soho

Solar A

Program: Solidaridad

Solidaridad 1

Solidaridad 2

Program: Solrad

Solrad 01

Solrad 03

Solrad 06A

Solrad 06B

Solrad 07A

Solrad 07B

Solrad 09

Solrad 10

Solrad 11A

Solrad 11B

Solwind

Program: Spacenet

Spacenet 1

Spacenet 2

Spacenet 3

Spacenet 3R

Program: Spartan

Spartan 101-1

Spartan 201-1

Spartan 201-2

Spartan 201-3

Spartan 204-1

Spartan 206-1

Program: Spas

Spas 1

Spas 2

Spas 3

Spas 4

Program: Spot

Spot 1

Spot 2

Spot 3

Program: Sputnik

Sputnik 01

Sputnik 02

Sputnik 03

Sputnik 04

Sputnik 05

Sputnik 06

Sputnik 07

Sputnik 09

Sputnik 10

Program: Sret

Sret 1

Sret 2

Program: Sross

Sross 1

Sross 2

Sross 3

Sross C2

Starlette

Start 1

Program: Statsionar

Statsionar 01

Statsionar 02

Statsionar 03

Statsionar 04

Statsionar 05

Statsionar 06

Statsionar 07

Statsionar 08

Statsionar 09

Statsionar 10

Statsionar 11

Statsionar 12

Statsionar 13

Statsionar 14

Statsionar 15

Statsionar 16

Statsionar 17

Statsionar 19

Statsionar 20

Statsionar 21

Statsionar 22

Statsionar 24

Statsionar 25

Statsionar 26

Statsionar 27

Stella

Program: Step

Step 1

Step 2

Step 3

Program: STRV

STRV 1A

STRV 1B

Surfsat 1

Program: Superbird

Superbird A1

Superbird A2

Superbird B1

Superbird D

Program: Symphonie

Symphonie 1

Symphonie 2

Program: Syncom

Syncom 1

Syncom 2

Syncom 3

T

Taiyo

Program: Tansei

Tansei 1

Tansei 2

Tansei 3

Tansei 4

TD 1A

Program: TDF

TDF 1

TDF 2

Program: TDRS

TDRS 1

TDRS 2

TDRS 3

TDRS 4

TDRS 5

TDRS 6

TDRS 7

TELE X

Program: Telecom

Telecom 1A

Telecom 1B

Telecom 1C

Telecom 2A

Telecom 2B

Telecom 2C

Program: Telstar

Telstar 1

Telstar 2

Telstar 301

Telstar 302

Telstar 303

Telstar 401

Telstar 402

Telstar 402R

Temisat

Program: Thaicom

Thaicom 1

Thaicom 2

Thor

Program: Tiros

Tiros 01

Tiros 02

Tiros 03

Tiros 04

Tiros 05

Tiros 06

Tiros 07

Tiros 08

Tiros 09

Tiros 10

Tiros N

Topex Poseidon

Tournesol

Traac

Program: Transit

Transit 2A

Transit 4A

Transit 4B

Transit 5BN1

Transit 5BN2

Program: Tsikada

Tsikada 1

TTS 1

TTS 2

Program: Tubsat

Tubsat A

Tubsat B

Program: Turksat

Turksat 1A

Turksat 1B

Program: Tvsat

Tvsat 1

Tvsat 2

U

UARS

Program: UHF

UHF 1

UHF 2

UHF 3

UHF 4

UHF 5

UHF 6

Ume 1

Ume 2

Unamsat 1

Program: Uosat

Uosat 1

Uosat 2

Uosat 3

Uosat 4

Uosat 5

UPMsat 1

Program: USA

V

Program: Vanguard

Vanguard 1

Vanguard 2

Vanguard 3

Program: Vela

Viking

Program: Vortex

Vortex 1

Vortex 2

Vortex 3

Vortex 4

Vortex 5

Vortex 6

W

Webersat

Program: Westar

Westar 1

Westar 2

Westar 3

Westar 4

Westar 5

Westar 6

Dial-Wika

Wind 1

Wresat

WSF 2

X

XTE

Y

Program: Yuri

Yuri 1

Yuri 2A

Yuri 2B

Yuri 2X

Yuri 3A

Yuri 3B

Yuri 3H

Yuri 3N


 Designation

Objects in space are tracked by the US Space Command. Each object is identified by 2 numbers called the Catalog Number (in the US Space Command database) and the International Launch number. You will find those 2 designators in the General section of each satellite sheet.

The Catalog Number is just an incremented number from the first object launched in space on. To search a satellite by its catalog number, use the search tool (keyword search) and enter "CATNR " followed by that number.

The International Launch Number is a code is composed of the year (2 first digits), by the number of the launch in the year (the 3 next digits) and 2 letters can be added to identify the objects resulting of a launch. Thus number 91026 means the 26th launch in 1991. To search for a launch by number, use the search tool (keyword search) and enter "LAUNR " followed by that number.

Last launches

1996

96019A	28 Mar	GPS BIIA-25

96018A	22 Mar	STS 76

96017A	21 Mar	IRS P3

96016A	14 Mar	Cosmos 2331

96015A	14 Mar	Intelsat 707

96014A	09 Mar	REX 2

96013A	24 Feb	Polar

96012B	26 Feb	TTS 2

96012A	22 Feb	STS 75

96011A	21 Feb	Soyuz TM-23

96010A	19 Feb	Raduga 33

96009F	19 Feb	Cosmos 2330

96009E	19 Feb	Cosmos 2329

96009D	19 Feb	Cosmos 2328

96009C	19 Feb	Gonets-D1 #?

96009B	19 Feb	Gonets-D1 #?

96009A	19 Feb	Gonets-D1 #?

96008A	17 Feb	NEAR

96____	14 Feb	Intelsat 708

96007A	05 Feb	N Star B

96006A	01 Feb	Palapa C1

96005A	25 Jan	Gorizont 31

96004A	16 Jan	Cosmos 2327

96003A	14 Jan	Koreasat 2

96002B	12 Jan	Measat 1

96002A	12 Jan	Panamsat 3R

96001B	11 Jan	Spartan 206-1

96001A	11 Jan	STS 72

1995

95074A	30 Dec	XTE

95073A	28 Dec	Echostar 1

95072B	28 Dec	Skipper

95072A	28 Dec	IRS 1C

95071A	20 Dec	Cosmos 2326

95070A	18 Dec	Progress M-30

95069A	15 Dec	Galaxy 3R

95068C	14 Dec	Cosmos 2325

95068B	14 Dec	Cosmos 2324

95068A	14 Dec	Cosmos 2323

95067B	06 Dec	Insat 2C

95067A	06 Dec	Telecom 2C

95066A	05 Dec	KH 12-3

95065A	02 Dec	Soho

95064A	28 Nov	Asiasat 2

95063A	17 Nov	Gals 2

95062A	17 Nov	ISO

95061A	12 Nov	STS 74

95060A	06 Nov	USA 115

95059B	04 Nov	Surfsat 1

95059A	04 Nov	Radarsat

95058A	31 Oct	Cosmos 2322

950___	23 Oct	Meteor (US)

95057A	22 Oct	UHF 6

95056A	20 Oct	STS 73

95055A	19 Oct	Astra 1E

95054A	11 Oct	Luch 1

95053A	08 Oct	Progress M-29

95052A	06 Oct	Cosmos 2321

95051A	29 Sep	Cosmos 2320

95050A	26 Sep	Resurs F20

95049A	24 Sep	Telstar 402R

95048C	11 Sep	WSF 2

95048B	08 Sep	Spartan 201-3

95048A	07 Sep	STS 69

95047A	03 Sep	Soyuz TM-22

95046A	31 Aug	Fasat Alfa

95046A	31 Aug	Sich 1

95045A	30 Aug	Cosmos 2319

95044A	29 Aug	N Star A

95043A	29 Aug	Jcsat 3

95____	15 Aug	Gemstar

95042A	09 Aug	Molniya 3-47

95041A	05 Aug	Koreasat 1

95040A	03 Aug	Panamsat 4

95039F	02 Aug	Magion 4

95039A	02 Aug	Prognoz 11

95038A	31 Jul	DSCS 3-09

95037C	24 Jul	Cosmos 2318

95037C	24 Jul	Cosmos 2317

95037A	24 Jul	Cosmos 2316

95036A	20 Jul	Progress M-28

95035B	13 Jul	TDRS 7

95035A	13 Jul	STS 70

95034A	10 Jul	USA 112

95033C	07 Jul	UPMsat 1

95033B	07 Jul	Cerise

95033A	07 Jul	Hélios 1A

95032A	05 Jul	Cosmos 2315

95031A	28 Jun	Cosmos 2314

95030A	27 Jun	STS 71

95____	22 Jun	Step 3

95029A	10 Jun	DBS 3

95028A	08 Jun	Cosmos 2313

95027A	31 May	UHF 5

95026A	24 May	Cosmos 2312

95025A	23 May	Goes 9

95024A	20 May	Spektr

95023A	17 May	Intelsat 706

95022A	14 May	USA 110

95021A	21 Apr	ERS 2

86017JE	19 Apr	GFZ 1

95020A	09 Apr	Progress M-27

95019A	07 Apr	AMSC 1

95018A	05 Apr	Offek 3

95017C	03 Apr	Microlab 1

95017B	03 Apr	Orbcomm FM2

95017A	03 Apr	Orbcomm FM1

95016B	28 Mar	Hotbird 1

95016A	28 Mar	Brazilsat B2

95___	28 Mar	Gurwin 1

95___	28 Mar	Unamsat 1

95___	28 Mar	EKA (Eksperimental'niy Kosmicheskiy Apparat)

95015A	24 Mar	DMSP B5D2-8

95014A	22 Mar	Cosmos 2311

95013A	22 Mar	Intelsat 705

95012A	22 Mar	Cosmos 2310

95011B	17 Mar	GMS 5

95011A	17 Mar	SFU

95010A	14 Mar	Soyuz TM-21

95009C	07 Mar	Cosmos 2309

95009B	07 Mar	Cosmos 2308

95009A	07 Mar	Cosmos 2307

95008A	02 Mar	Cosmos 2306

95007A	02 Mar	STS 67

95006A	16 Feb	Foton 10

95005A	15 Feb	Progress M-26

95004H	04 Feb	Oderacs 2F

95004G	04 Feb	Oderacs 2E

95004F	04 Feb	Oderacs 2D

95004E	04 Feb	Oderacs 2C

95004D	04 Feb	Oderacs 2B

95004C	04 Feb	Oderacs 2A

95004B	07 Feb	Spartan 201-2

95004A	03 Feb	STS 63

95003A	29 Jan	UHF 4

95002C	24 Jan	Faisat

95002B	24 Jan	Astrid

95002A	24 Jan	Tsikada 1

95____	15 Jan	EXPRESS (German) (no number given)

95001A	10 Jan	Intelsat 704

1994

94089A	30 Dec	NOAA 14

94088A	29 Dec	Cosmos 2305

94087A	28 Dec	Raduga 32

94086F	26 Dec	Cosmos 2304

94086E	26 Dec	Cosmos 2303

94086D	26 Dec	Cosmos 2302

94086C	26 Dec	Cosmos 2301

94086B	26 Dec	Cosmos 2300

94086A	26 Dec	Cosmos 2299

94085A	26 Dec	RS 15

94084A	22 Dec	DSP 3-5

94083A	20 Dec	Cosmos 2298

94082A	16 Dec	Luch 0

94081A	14 Dec	Molniya 1-88

94____	01 Dec	Panamsat 3

94080A	29 Nov	Dong Fang Hong 41

94079A	29 Nov	Orion 1

94078A	24 Nov	GEO-IK

94077A	24 Nov	Cosmos 2297

94076C	20 Nov	Cosmos 2296

94076B	20 Nov	Cosmos 2295

94076A	20 Nov	Cosmos 2294

94075A	11 Nov	Progress M-25

94074A	04 Nov	Resurs O1-3

94073B	04 Nov	Spas 4 (Crista)

94073A	03 Nov	STS 66

94072A	02 Nov	Cosmos 2293

94071A	01 Nov	Wind 1

94070A	01 Nov	Astra 1D

94069A	31 Oct	Electro 1

94068A	15 Oct	IRS P2

94067A	13 Oct	Express 01

94066A	11 Oct	Ocean 4

94065B	08 Oct	Thaicom 2

94065A	08 Oct	Solidaridad 2

94064A	06 Oct	Intelsat 703

94063A	03 Oct	Soyuz TM-20

94062A	30 Sep	STS 68

94061A	27 Sep	Cosmos 2292

94060A	21 Sep	Cosmos 2291

94059B	13 Sep	Spartan 204-1

94059A	09 Sep	STS 64

94058A	09 Sep	Telstar 402

94057A	29 Aug	DMSP B5D2-7

94056A	28 Aug	ETS 6

94055A	27 Aug	Optus B3

94054A	27 Aug	USA 105

94053A	26 Aug	Cosmos 2290

94052A	25 Aug	Progress M-24

94051A	23 Aug	Molniya 3-46

94050C	11 Aug	Cosmos 2289

94050B	11 Aug	Cosmos 2288

94050A	11 Aug	Cosmos 2287

94049B	11 Aug	Turksat 1B

94049A	11 Aug	Brazilsat B1

94048A	05 Aug	Cosmos 2286

94047A	03 Aug	DBS 2

94046A	03 Aug	Apex

94045A	02 Aug	Cosmos 2285

94044A	29 Jul	Cosmos 2284

94043A	21 Jul	Apstar 1

94042A	20 Jul	Cosmos 2283

94041A	14 Jul	Nadezhda 4

94040B	08 Jul	Yuri 3N

94040A	08 Jul	Panamsat 2

94039A	08 Jul	STS 65

94038A	06 Jul	Cosmos 2282

94037A	03 Jul	Dong Fang Hong 40

94036A	01 Jul	Soyuz TM-19

94____	27 Jun	Step 1

94035A	24 Jun	UHF 3

94034C	17 Jun	STRV 1B

94034B	17 Jun	STRV 1A

94034A	17 Jun	Intelsat 702

94033A	14 Jun	Foton 09

94032A	07 Jun	Cosmos 2281

94____	25 May	Cosmos

94031A	22 May	Progress M-23

94030A	20 May	Gorizont 30

94029A	19 May	Step 2

94028A	09 May	MSTI 2

94027A	04 May	Sross C2

94026A	03 May	USA 103

94025A	28 Apr	Cosmos 2280

94024A	26 Apr	Cosmos 2279

94023A	23 Apr	Cosmos 2278

94022A	13 Apr	Goes 8

94021C	11 Apr	Cosmos 2277

94021B	11 Apr	Cosmos 2276

94021A	11 Apr	Cosmos 2275

94020A	09 Apr	STS 59

94019A	22 Mar	Progress M-22

94018A	17 Mar	Cosmos 2274

94017B	13 Mar	USA 102

94017A	13 Mar	USA 101

94016B	10 Mar	Seds 2

94016A	10 Mar	GPS BIIA-24

94015A	04 Mar	STS 62

94014A	02 Mar	Koronas 1

94013A	19 Feb	Galaxy 1R

94012A	18 Feb	Raduga 31

94011F	12 Feb	Cosmos 2273

94011E	12 Feb	Cosmos 2272

94011D	12 Feb	Cosmos 2271

94011C	12 Feb	Cosmos 2270

94011B	12 Feb	Cosmos 2269

94011A	12 Feb	Cosmos 2268

94010B	08 Feb	Dong Fang Hong 39

94010A	08 Feb	Dong Fang Hong 38

94009A	07 Feb	USA 099

94008A	05 Feb	Raduga 1-3

94007B	03 Feb	Ryusei (OREX)

94007A	03 Feb	Myojo (VEP)

94006H	09 Feb	Bremsat

94006G	09 Feb	Oderacs 1F

94006F	09 Feb	Oderacs 1E

94006E	09 Feb	Oderacs 1D

94006D	09 Feb	Oderacs 1C

94006C	09 Feb	Oderacs 1B

94006B	09 Feb	Oderacs 1A

94006A	03 Feb	STS 60

94005A	28 Jan	Progress M-21

94004A	25 Jan	DSPSE (Clementine)

94003A	25 Jan	Meteor 3-06

94003B	25 Jan	Tubsat B

94____	24 Jan	Turksat 1A

94____	24 Jan	Eutelsat 2F5

94002A	20 Jan	Gals 1

94001A	08 Jan	Soyuz TM-18

1993

93079A	22 Dec	Molniya 1-87

93078B	18 Dec	Thaicom 1

93078A	18 Dec	DBS 1

93077A	16 Dec	Telstar 401

93076A	08 Dec	Nato 4B

93075A	02 Dec	STS 61

93074A	28 Nov	DSCS 3-08

93073B	20 Nov	Meteosat 6

93073A	20 Nov	Solidaridad 1

93072A	18 Nov	Gorizont 29

93071A	05 Nov	Cosmos 2267

93070A	02 Nov	Cosmos 2266

93069A	28 Oct	Gorizont 28

93068A	26 Oct	GPS BIIA-23

93067A	26 Oct	Cosmos 2265

93066A	22 Oct	Intelsat 701

93065A	18 Oct	STS 58

93064A	11 Oct	Progress M-20

93063A	08 Oct	Dong Fang Hong 37

93____	05 Oct	Landsat 6

93062A	30 Sep	Raduga 30

93061H	26 Sep	Kitsat B

93061G	26 Sep	Posat

93061E	26 Sep	Healthsat

93061D	26 Sep	Itamsat

93061C	26 Sep	Eyesat

93061B	26 Sep	Stella

93061A	26 Sep	Spot 3

93____	20 Sep	IRS 1E

93060A	17 Sep	Cosmos 2264

93059A	16 Sep	Cosmos 2263

93058C	13 Sep	Spas 3

93058B	12 Sep	ACTS

93058A	12 Sep	STS 51

93057A	07 Sep	Cosmos 2262

93056A	03 Sep	UHF 2

93055C	31 Aug	Temisat

93055A	31 Aug	Meteor 2-21

93054A	30 Aug	GPS BIIA-22

93053A	24 Aug	Resurs F19

93052A	10 Aug	Progress M-19

93051A	10 Aug	Cosmos 2261

93050A	09 Aug	NOAA 13

93049A	04 Aug	Molniya 3-45

93____	02 Aug	NOSS 14

93048B	22 Jul	Insat 2B

93048A	22 Jul	Hispasat 1B

93047A	22 Jul	Cosmos 2260

93046A	19 Jul	DSCS 3-07

93045A	14 Jul	Cosmos 2259

93044A	07 Jul	Cosmos 2258

93043A	01 Jul	Soyuz TM-17

93042B	26 Jun	PMG

93042A	26 Jun	GPS BIIA-21

93041A	25 Jun	Radcal

93040A	25 Jun	Resurs F18

93039A	25 Jun	Galaxy 4

93038F	20 Jun	Cosmos 2257

93038E	20 Jun	Cosmos 2256

93038D	20 Jun	Cosmos 2255

93038C	20 Jun	Cosmos 2254

93038B	20 Jun	Cosmos 2253

93038A	20 Jun	Cosmos 2252

93037A	21 Jun	STS 57

93036A	16 Jun	Cosmos 2251

93____	27 May	Gorizont #39

93035A	26 May	Molniya 1-86

93034A	22 May	Progress M-18

93033A	21 May	Resurs F17

93032A	13 May	GPS BIIA-20

93031B	12 May	Arsène

93031A	12 May	Astra 1C

93030F	11 May	Cosmos 2250

93030E	11 May	Cosmos 2249

93030D	11 May	Cosmos 2248

93030C	11 May	Cosmos 2247

93030B	11 May	Cosmos 2246

93030A	11 May	Cosmos 2245

93029A	28 Apr	Cosmos 2244

93028A	27 Apr	Cosmos 2243

93027A	26 Apr	STS 55

93026A	25 Apr	Alexis

93025A	21 Apr	Molniya 3-44

93024A	16 Apr	Cosmos 2242

93023B	11 Apr	Spartan 201-1

93023A	08 Apr	STS 56

93022A	06 Apr	Cosmos 2241

93021A	02 Apr	Cosmos 2240

93020A	01 Apr	Cosmos 2239

93019A	31 Mar	Progress M-17

93018A	30 Mar	Cosmos 2238

93017B	30 Mar	Seds 1

93017A	30 Mar	GPS BIIA-19

93016A	26 Mar	Cosmos 2237

93015A	25 Mar	UHF 1

93014A	25 Mar	Start 1

93013A	25 Mar	Raduga 29

93012A	21 Feb	Progress M-16

93011A	20 Feb	Astro D

93010C	17 Feb	Cosmos 2236

93010B	17 Feb	Cosmos 2235

93010A	17 Feb	Cosmos 2234

93009B	09 Feb	SCD

93009A	09 Feb	Orbcomm XP 1

93008A	09 Feb	Cosmos 2233

93007A	03 Feb	GPS BIIA-18

93006A	26 Jan	Cosmos 2232

93005A	24 Jan	Soyuz TM-16

93004A	19 Jan	Cosmos 2231

93003B	13 Jan	TDRS 6

93003A	13 Jan	STS 54

93002A	13 Jan	Molniya 1-85

93001A	12 Jan	Cosmos 2230

1992

92095A	29 Dec	Cosmos 2229 (bion 10)

92094A	25 Dec	Cosmos 2228

92093A	25 Dec	Cosmos 2227

92092A	22 Dec	Cosmos 2226

92091A	22 Dec	Cosmos 2225

92090A	21 Dec	Optus B2

92089A	18 Dec	GPS BIIA-17

92088A	17 Dec	Cosmos 2224

92087A	09 Dec	Cosmos 2223

92086B	02 Dec	USA 089

92086A	02 Dec	STS 53

92085A	02 Dec	Molniya 3-

92084A	01 Dec	Superbird A2

92083A	28 Nov	KH 12-2

92082A	27 Nov	Gorizont 27

92081A	25 Nov	Cosmos 2222

92080A	24 Nov	Cosmos 2221

92079A	23 Nov	GPS BIIA-16

92078A	21 Nov	MSTI 1

86017GX	20 Nov	Mak 2

92077A	20 Nov	Cosmos 2220

92076A	17 Nov	Cosmos 2219

92075A	15 Nov	Resurs 500

92074A	30 Oct	Ekran 20

92073A	29 Oct	Cosmos 2218

92072A	28 Oct	Galaxy 7

92071A	27 Oct	Progress M-15

92070C	31 Oct	CTA

92070B	23 Oct	Lageos 2

92070A	22 Oct	STS 52

92069A	21 Oct	Cosmos 2217

92068F	20 Oct	Cosmos 2216

92068E	20 Oct	Cosmos 2215

92068D	20 Oct	Cosmos 2214

92068C	20 Oct	Cosmos 2213

92068B	20 Oct	Cosmos 2212

92068A	20 Oct	Cosmos 2211

92067A	14 Oct	Molniya 3-42

92066A	12 Oct	DFS 3

92065A	08 Oct	Foton

92064B	06 Oct	Dong Fang Hong 36

92064A	06 Oct	Freja

92063A	25 Sep	Mars Observer

92062A	22 Sep	Cosmos 2210

92061A	12 Sep	STS 47

92060B	10 Sep	Satcom C3

92060A	10 Sep	Hispasat 1A

92059A	10 Sep	Cosmos 2209

92058A	09 Sep	GPS BIIA-15

92057A	31 Aug	Satcom C4

92____	22 Aug	Galaxy 1R failure

92056D	19 Aug	Pion 2

92056C	19 Aug	Pion 1

92056A	19 Aug	Resurs F16

92055A	15 Aug	Progress M-14

92054A	13 Aug	Optus B1

92053A	12 Aug	Cosmos 2208

92052C	10 Aug	S80T

92052B	10 Aug	Kitsat A

92052A	10 Aug	Topex Poseidon

92051A	09 Aug	Dong Fang Hong 35

92050A	06 Aug	Molniya 1-

92049B	31 Jul	Eureca 1

92049A	31 Jul	STS 46

92048A	30 Jul	Cosmos 2207

92047C	29 Jul	Cosmos 2206

92047B	29 Jul	Cosmos 2205

92047A	29 Jul	Cosmos 2204

92046A	27 Jul	Soyuz TM-15

92045A	24 Jul	Cosmos 2203

92044B	24 Jul	DUVE

92044A	24 Jul	Geotail

92043A	14 Jul	Gorizont 26

92042F	13 Jul	Cosmos 2202

92042E	13 Jul	Cosmos 2201

92042D	13 Jul	Cosmos 2200

92042C	13 Jul	Cosmos 2199

92042B	13 Jul	Cosmos 2198

92042A	13 Jul	Cosmos 2297

92041B	09 Jul	Eutelsat 2F4

92041A	09 Jul	Insat 2A

92040A	08 Jul	Cosmos 2196

92039A	07 Jul	GPS BIIA-14

92038A	03 Jul	Sampex

92037A	02 Jul	DSCS 3-06

92036A	01 Jul	Cosmos 2195

92035A	30 Jun	Progress M-13

92034A	25 Jun	STS 50

92033A	23 Jun	Resurs F15

92032A	09 Jun	Intelsat K

92031A	07 Jun	EUVE

92030H	02 Jun	Cosmos 2194

92030G	02 Jun	Cosmos 2193

92030F	02 Jun	Cosmos 2192

92030E	02 Jun	Cosmos 2191

92030D	02 Jun	Cosmos 2190

92030C	02 Jun	Cosmos 2189

92030B	02 Jun	Cosmos 2188

92030A	02 Jun	Cosmos 2187

92029A	28 May	Cosmos 2186

92028A	20 May	Sross 3

92027A	14 May	Palapa B4

92026A	07 May	STS 49

92025A	29 Apr	Cosmos 2185

92024A	29 Apr	Resurs F14

92023A	25 Apr	USA 081

92022A	19 Apr	Progress M-12

92021B	15 Apr	Inmarsat 2F4

92021A	15 Apr	Telecom 2B

92020A	15 Apr	Cosmos 2184

92019A	10 Apr	GPS BIIA-13

92018A	08 Apr	Cosmos 2183

92017A	02 Apr	Gorizont 25

92016A	01 Apr	Cosmos 2182

92015A	24 Apr	STS 45

92014A	17 Mar	Soyuz TM-14

92013A	14 Mar	Galaxy 5

92012A	09 Mar	Cosmos 2181

92011A	04 Mar	Molniya 1-

92010B	26 Feb	Arabsat 1C

92010A	26 Feb	Superbird B1

92009A	23 Feb	GPS BIIA-12

92008A	17 Feb	Cosmos 2180

92007A	11 Feb	JERS 1

92006A	10 Feb	DSCS 3-05

92____	05 Feb	Cosmos FTO

92005C	29 Jan	Cosmos 2179

92005B	29 Jan	Cosmos 2178

92005A	29 Jan	Cosmos 2177

92004A	25 Jan	Progress M-11

92003A	24 Jan	Cosmos 2176

92002A	22 Jan	STS 42

92001A	21 Jan	Cosmos 2175


 Tag's Broadcasting Services

This file is shareware, belongs to TBS-satellite (Jean-Philippe Donnio), © all rights reserved, 1993-1996.

Section en français

Also to be read:

License Agreement

Bibliography reference

Acknowledgment

Versions

Compatible software

Help: how to use this encyclopedia?

Philosophy of this encyclopedia

This satellite encyclopedia is aimed to gather knowlegde into a single easy to use document. Contributions are welcome... You may even become a coauthor of TSE like Jean-Jacques Serra who manages the launch vehicle section! This encyclopedia is published every 3 months. Therefore this software is not a final version!

If you are any kind of satellite specialist, satellite operator or constructor, or a space organization we would be very glad to get in touch with you. If for some reason you feel we are not treating your organization's satellites correctly, understand we only work with data we have! Operators are encouraged to send their Technical User Guide and other technical documentations, including preliminary data when available.

If you are the author of a satellite related book or software, or if your organization publishes a magazine or newsletter related to space or satellite, see my special offer in the license agreement.

Pass this encyclopedia around: the more people it'll reach, the larger it'll grow!

The fair play

This encyclopedia is shareware: you can use it on a trial basis during SEVEN days; after this delay you should either register or delete it. The shareware version is size-limited to fit on a 3.5" floppy. Thus numerous EIRP maps are not included so as the Cosmos program. That's why you get an error when clicking on those items.

If you use The Satellite's Encyclopedia after 7 days of trial or for commercial purposes, you MUST register. The registered version includes:

the full 5.2 MB help file with:

245 EIRP maps

the listing of satellites on the Clarke Belt

the calendar with the future launches and details about the related satellites

the Russian programs

TSE is like a magazine: the shareware version is like the copy of a magazine you read at the bookshop. Buying this copy is like registering a single issue of TSE. Registering TSE with the subscription option gives you 4 full issues (one year) which is similar to subscribing to the bookshop magazine. Turn to the license agreement for more details.

In any case, this encyclopedia remains my property. No reverse engineering No reprint

How to obtain the latest release?

1°/ By registering: see the license agreement

2°/ By downloading:

Internet: see the list of ftp sites at http://www.TELE-satellit.com/tse/  The primary ftp site for TSE is ftp://ftp.TELE-satellit.com/pub/tse/

3°/ Via any good shareware dealer

Online support

Online support is available from the internet via our web server at http://www.TELE-satellit.com/tse/

The online version of TSE is located at http://www.TELE-satellit.com/tse/online/  Check it out for the latest updates of TSE!

You may also subscribe to our mailing lists by email or online. To join the public mailing list, send an email:

To: majordomo@tags1.dn.net

Subject: none

Body: subscribe tse-pub

A development list is also available under the name tse-dev

Contact

Jean-Philippe Donnio

Tag's Broadcasting Services

2 allée des îles

F-14123 Fleury/Orne

France

jpdonnio@tags1.dn.net

Please mention the version of the encyclopedia you currently use.

Providing data

We need:

Your name or alias (that will be quoted in the aknowledgment section)

Your postal address (and electronic if you have any)

The information with it's precise origin & date

The version of the encyclopedia you currently use

You will be thanked with the latest version of the encyclopedia.


 License Agreement

Please feel free to upload this software to any electronic bulletin board, demonstrate the software and its capabilities or give copies to potential users, so that others may have the opportunity to obtain a copy for use in accordance with the license terms contained in this file.

Credit Card order form without VAT

Credit Card order form with VAT

Alternative order form

License Agreement

The use of The Satellite's Encyclopedia is subject to the following terms and conditions.

The Satellite's Encyclopedia is copyrighted material. It is protected by the French copyright laws. You may not make any changes or modifications to The Satellite's Encyclopedia. You may not decompile, disassemble, or otherwise reverse-engineer the software in any way. No reproduction whatever the method.

You may use The Satellite's Encyclopedia on a trial basis provided you do not violate the protection afforded the licensed software by the copyright laws, and you agree to the terms of the license agreement. You are entitled to evaluate the software freely for SEVEN days. If you use The Satellite's Encyclopedia further on or for COMMERCIAL PURPOSES, you must purchase a license for its use. If you don't use it, delete it.

How much is a license:

See the order forms above. Registration provides you with a personal most updated version which includes:

the full 5.2 MB help file with:

245 EIRP maps

the listing of satellites on the Clarke Belt

the calendar with the future launches and details about the related satellites

the Russian programs

Subscriptions (4 issues) are also available.

Special offers:

If you are a firm that publishes an electronic or paper periodical related to satellite (in French, English or German) you may obtain a free registration and a 1 year update subscription against a free one-year subscription to your publication.

If you are the author of a book related to satellite (in French, English or German) you may obtain a free registration and a 1 year update subscription against a free copy of your book.

If you are the author of a shareware related to satellite (in French, English or German) you may obtain a free registration and a 1 year update subscription against a free license for your shareware.

Please note we reserve the right to refuse your application.

Title to the licensed software is not transferred to the end user. The end-user is granted an non exclusive license to use the software on one computer or computer workstation at any given time. Moreover he agrees to only copy the software for backup purpose.

Limited Warranty

While every precaution has been taken in the compilation of this data, the publisher assumes no responsability for errors or omissions. Neither is any liability assumed for damages resulting from the use of the information contained herein.

We shall not be responsible for any problems or damage caused by the licensed software that may result from using the licensed software. This includes, but is not limited to, computer hardware, computer software, operating systems, and any computer or computing accessories. End user agrees not to hold me responsible for any problems arising from the use of the software.

We shall not in any case be liable for any special, incidental, consequential, indirect or other similar damages arising from any breach of these warranties even if we have been advised of the possibility of such damages.

In no case shall my liability exceed the license fees paid for the right to use the licensed software.

In the event of invalidity of any provision of this license, the parties agree that such invalidity shall not affect the validity of the remaining portions of this license.

The Satellite's Encyclopedia's Distribution

The Satellite's Encyclopedia must be copied in an unmodified form and must contain all the files required for an automatic installation. No fee, charge or other compensation may be accepted or requested by anyone without my express written permission.

Public Domain disk vendors may not charge a fee for The Satellite's Encyclopedia itself. However you may include The Satellite's Encyclopedia on a diskette or CD-ROM for which you charge a nominal distribution fee. If it is included on a CD-ROM you must send me a free copy of this CD-ROM. The purchaser of said media must be informed in advance that the fee paid to acquire the media does not relieve said purchaser from paying the registration fee for The Satellite's Encyclopedia if said purchaser uses The Satellite's Encyclopedia.

Operators of electronic Bulletin Board Systems (sysops) may post The Satellite's Encyclopedia for downloading by their users without written permission only as long as the above conditions are met. A fee may be charged for access to the BBS as long as no specific fee is charged for downloading The Satellite's Encyclopedia files without first obtaining express written permission from myself to charge such a fee. This also goes for Internet and Compuserve; other online services must apply for authorization. As far as the French Minitel is concerned, operators are NOT allowed to offer downloading of The Satellite's Encyclopedia.

The above constitutes the license agreement for The Satellite's Encyclopedia. It supersedes any and all previous license agreements.


Order form
 Credit card order form without VAT

V0.34.001

CAUTION: this order form is only applicable if you are out of European

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If you fax this form, please write in ALL CAPS


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 Credit card order form with VAT

V0.34.001

FROM:

      Name: ______________________________________________________

 [Company]: ______________________________________________________

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            [Used to register your software, 25 characters max]

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            Phone: +33-8730-8557     Fax: +33-8732-3775

            Email: 100031.3257@compuserve.com

If you fax this form, please write in ALL CAPS


 Alternative order form

V0.34.001

FROM:

      Name: ______________________________________________________

 [Company]: ______________________________________________________

  Reg Name: ______________________________________________________

            [Used to register your software, 25 characters max]

   Address: ______________________________________________________

      City: ____________________________ Postal Code: ____________

   Country: ____________________________ [State]: ________________

     Phone: ________________________ Fax: ________________________

     Email: ______________________________________________________

Single issue with floppies (airmail)

at FRF 100 each........................................___x 100   ______

Single issue via Internet (ftp download)

at FRF 80 each.........................................___x  80   ______

Four issues with floppies (airmail)

at FRF 300 each........................................___x 300   ______

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PAYMENT (only FRF accepted; payable to Jean-Philippe Donnio):

( ) Check (must be drawn on a French bank)

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Date: ________________________________

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SEND TO:

            Jean-Philippe Donnio

            2 allée des îles

            F-14123 Fleury/Orne

            France


 Bibliography

Books

Atlas de géographie de l'Espace (Fr)

Sous la direction de F. Verger, avec Isabelle Sourbès, Raymond Ghirardi et Yvette Palazot

SIDES / RECLUS, 1992

ISBN 2-86861-080-3 / 2-86912-044-1

Encyclopédie Internationale des Sciences et des Techniques (Fr)

1972

L'escalade du Cosmos (Fr)

Patrick Maurel

Bordas, 1972

L'état des sciences et des techniques (Fr)

Sous la direction de Nicolas Witkowski

La découverte, 1991

ISBN 2-7071-2069-3

Fusées et Astronautique (Fr)

Camille Rougeron et Jean Bodet

Larousse, 1964

Les fusées et missiles d'aujourd'hui (Fr)

Bill Gunston, translated from The Illustrated Encyclopedia of the World's Rockets & Missiles

Elsevier, 1979

ISBN 2-8003-0351-4

Grand Atlas de l'Espace (Fr)

Universalis, 1988

ISBN 2-85229-910-0

Le Guide des Lanceurs Spatiaux (Fr)

Serguei Grichkov

Tessier & Ashpool Ltd, 1992

ISBN 2-9094-6700-7

History of Liquid Rocket Engines - Development in the United States (Eng)

Stephen E. Doyle

American Astronautical Society 1992

ISBN 0-87703-350-1

L'Homme, l'Air et l'Espace (Fr)

Charles Bollfis, Henry Beauboir, Camille Rougeron

Édition de l'illustration, 1965

Matra Marconi Space Earth Observation Directory (Eng)

1993/94 edition

Matra Marconi Space European Spacecraft Directory (Eng)

3rd edition, 1992

Matra Marconi Space World Spacecraft Directory (Eng)

1993/94 edition

Réception TV par satellites (Fr)

René Besson

Dunod, Paris, 1992

ISBN 2-10-001462-5

Rockets into Space (Eng)

Frank H. Winter

Harvard University Press, 1990

ISBN 0-674-77660-7

La science au présent (Fr)

Encyclopædia Universalis, 1992

ISBN 2-85229-501-6

Les systèmes de télécommunications par satellite (Fr)

G. Maral, M. Bousquet, J. Pares

Masson, Paris, 1982

ISBN 2-225-75284-2

Les trente premières années du CNES (Fr)

Claude Carlier and Marcel Gilli

La documentation française, 1994

ISBN 2-11-003206-5

L'univers satellite, Guide pratique de la réception satellite (Fr)

Edition 91/92

Media Presse Information (MPI), 1991

ISBN 2-9505754-0-4

The Illustrated Encyclopedia of the World's Rockets & Missiles (Eng)

Bill Gunston

Salamander Books Ltd, London, 1979

ISBN 0-517-26870-1

Word Radio TV Handbook (Eng)

1993 edition

Billboard Books

WRTH Satellite Broadcasting Guide 1994 (Eng)

Bart Kuperus

Billboard Books

ISBN 0-8230-5954-5

WRTH Satellite Broadcasting Guide 1995 (Eng)

Bart Kuperus

Billboard Books

ISBN 0-8230-5955-3

Paper periodicals

Air & Cosmos (Fr)

ISSN 1240-3113

Arianespace Newsletter (Eng)

ISSN 0984-8452

Infosat (Ger)

ISSN 0933-6907

Megahertz Magazine (Fr)

ISSN 0755-4419

Revue des Télécoms (Fr)

ISSN 0183-8636

Satellites Infos (Fr)

ISSN n/a

Satellite TV Magazine (Fr)

ISSN 0985-1542

Sciences et Avenir (Fr)

ISSN n/a

TELE-satellit (Ger)

ISSN 0943-9137

Télé Satellite (Fr)

ISSN n/a

Electronic periodicals

Jonathan's Space Report (Eng)

By Jonathan McDowell <jmcdowell@cfa.harvard.edu>

MediaScan (Eng)

From Radio Sweden <wood@stab.sr.se>

Space news from Aviation Week & Space Technology (Eng)

By Henry Spencer <henry@zoo.toronto.edu>

Satellite Journal International (Eng)

Contact: <71165.2032@compuserve.com>

South Scanner Satellite Services Chart (Eng)

By Robert Smathers <roberts@nmia.com>

Space Calendar (Eng)

By Ron Baalke <baalke@kelvin.jpl.nasa.gov>

SpaceNews (Eng)

By John A. Magliacane <kd2bd@amsat.org>

Spacewarn Bulletin (Eng)

From National Space Science Data Center <sardi@nssdc.gsfc.nasa.gov>

http://nssdc.gsfc.nasa.gov/spacewarn/spacewarn.html

SAT News Desk (Ger)

By Peter C. Klanowski <pck@lynet.de>

TELE-satellit News (Eng)

By Martyn Williams <martyn@twics.com>


Acknowlegdment
 Acknowledgment

In this section we want to thank all those who collaborated to improve The Satellite's Encyclopedia. Please also check the compatible software section.

Co-authors

Jean-Jacques Serra

Gunter Krebs

Special thanks

Curt Swinehart

Curt is our information center! When something is going on related to satellite somewhere in the world, he's back with the press releases. Curt also monitors activity on the Internet. He is a vital resource to TSE! You may contact him at cswineha@emerald.tufts.edu

TELE-satellit

A monthly satellite magazine edited in Munich, Germany. It consists of 192 pages, full color with tables, charts and news with many off-screen photos of the satellite channels plus an informative technical section. Simply the best for satellite TV! For further details about TELE-satellit order a sample copy at: TELE-satellit customer service, Silheimerstr. 6a, D-89278 Nersingen, Fax +49-7308-919001, 100543.660@compuserve.com. Have a look a the web site: http://www.TELE-satellit.com

Satellite TV Club

A French club that promotes satellite TV and organizes a yearly satellite event in May. It gathers amateurs and specialists. The club compiles a weekly program chart devoted to language study via Astra, very useful to teachers. Maintains the Minitel 3615 SATTV service. For further details contact: Satellite TV Club, Place de Mons, F-33360 CENAC

Data providers - Thanks!

Date	Provider	Description
Mar 1996	Jean-Claude Mermilliod <mermio@scsun.unige.ch>	Hipparcos data correction
Feb 1996	Reinhard Richter, DJ1KM <dj1km@amsat.org>	Phase 3D data
Jan 1996	Keith Stein <us011192@interramp.com>	Frequency information
Jan 1996	Rainer Kracht <R.Kracht@t-online.de>	Radioactive debris information
Jan 1996	Tom KAWAI <tom@venture-web.or.jp>	Jcsat 4 information
Aug 1995	Optus Communications	Optus' Satellite Network Designer's Guide
Jul 1995	Intersputnik	Intersputnik User handbook and footprints
Jul 1995	Didier Dausmann	HAM satellite frequency listing
Jul 1995	Bruno Tilgner <btilgner@esa.bitnet>	ESA information
Apr 1995	Curt Swinehart <cswineha@emerald.tufts.edu>	Satellite operators information sheet Feeds me with satellite press releases
Apr 1995	Anna Laurin <aln@ssc.se>  and Olle Norberg <Olle.Norberg@irf.se>	Astrid info
Mar 1995	Stuart A. MacMillan	Info on Telesat Canada's satellites
Mar 1995 on	Jonathan McDowell <jmcdowell@cfa.harvard.edu>	JSR weekly news update and JSR back issues. Special thanks for all his help answering my numerous questions!
24 Feb 1995	Daniel Audeon	Astronautique 1, a database he built containing astronauts and manned launches.
Feb 1995 on	Dr TS Kelso Adjunct Professor of Space Operations <tkelso@afit.af.mil>	Provides me TLE from the Air Force Institute of Technology database
24 Nov 1994	Jean-Claude Durand Club Européen de DX Radio TV	Payload description of flights 40-44, 46-56, 58-63, 65-70 of Ariane
25 Jul 1994	Franck Nony	Matra Marconi Space European Spacecraft Directory 1992
23 Jul 1994	Satellite TV Club	Documentation on Loutch, Coupon, Rimsat, Gorizont 17, Astra, Thor, Panamsat, Orion, etc. satellites
23 Jul 1994	Pierre A. Sicart	Matra Marconi Space Earth Observation Directory 1993/94 Matra Marconi Space World Spacecraft Directory 1993/94
5 Jul 1994	Robert Smathers <roberts@nmia.com>	Enabled me to include data from his South Scanner Satellite Services Chart
Bugs hunters

Romain Guesdon <romain.guesdon@p6.f10.n322.z2.fidonet.org>

Nemo

Philippe Plumecocq

Progfou <progfou@tags1.dn.net>


 Versions

Version	Release date	Comments
0.34.001	10 Apr 1996	First release of TSE Winhelp with TSE Online (http://www.tele-satellit.com/tse/online/)
0.33.001	15 Dec 1995	Extension of the launcher section and the launch calendar (including details on future satellites) Added numerous EIRP maps TSE can be called from WinOrbit 2.7 and upper (freeware tracking program)
0.32.001	1 Sep 1995	First in History section Numerous launch programs added especially Atlas Support mailing list available New EIRP maps
0.31.001	1 Jun 1995	New CDROM distribution policy (compilers must send me a free copy) No Minitel distribution allowed Added numerous EIRP maps Introduced the full International Designator number
0.30.001	1 Mar 1995	Included a calendar of future launches Included a list of spacecrafts on the Clarke Belt Maps were redrawn and North-American satellites were added STS flights coverage was improved Added order forms and credit card registration
0.22.001	1 Dec 1994	New license agreement, data update
0.21.001	20 Sep 1994	Fixes numerous typos due to translation
0.20.001	12 Sep 1994	Translation in English
0.10.001	1 Sep 1994	Thematic index for missions Last French version
0.09.001	1 Jul 1994	Integrity checking with NASA's catalog number Technical data for geostationary telecommunication satellites
0.08.001	1 Jun 1994	Introduction of NASA's catalog & launch number
0.07.001	13 Apr 1994	First STS missions
0.06.001	7 Feb 1994	Modification of the maps Bug correction
0.05.001	17 Jan 1994	License agreement, first public release


 Compatible software

The Satellite's Encyclopedia is compatible with some windows based software. This enables you to call your favorite satellite reference from those fine products with a single keystrike! Here is a list of those products with a description:

Logsat

This is a shareware tracking program which offer numerous goodies to ease your everyday monitoring. It handles an elements database and cares about the updates. It provides a logbook and a callbook to hold your records. It also provides antenna and propagation utilities.

You can get the full information on Logsat from http://www.netwide.net/logsat or contact Logsat by mail: logsat@netwide.net

Satmaster

This is a satellite tool box gathering all you need to install a satellite dish and design a reception station (from personal dish to ground earth station). It can calculate link budgets (analog, digital, SCPC) so as all kind of look angles. Moreover giving parameters of your reception station it will tell you the diameter of the dish you need to get a signal. It is ready to use with a database of towns around the globe.

You can get more information from here: http://www.connect.org.uk/merseymall/Arrowe/ (where a freeware version is available) or contact its author at djsteph@arrowe.u-net.com

WinOrbit

This is a program for computing artificial Earth-satellite position and visibility, with the Amateur Radio Satellite operator in mind. Quite simple to use it can operate with several different calculation models. Moreover it is freeware!

You can find the full documentation of Winorbit at http://www.sat-net.com/winorbit/ so as download the software. You can contact its author at cgregory@uiuc.edu


 How to use this encyclopedia?

If you never used a help file before and want to know more about them, press F1

Glossary

Help on printing

What's hypertext?

Hypertext is a set of electronic textual data that can be read different ways. Data is distributed in items that are not attached like cars of a train but marked with links which enable passage from one another when the user activates them. Links are attached to words or to images.

Using hypertext links

Hypertext is very useful to enable the reader to define its own way through data.

The hypertext sensitive zones are generally in green (it may change) and underlined. You can press CTRL+TAB to see all of them. To active one, just click.

For example, on a satellite sheet you may click for data on its country of origin, mission, launch vehicle, etc. You also can access the program it belongs to (if it exists of course) by clicking the upper left icon.

Organization of the encyclopedia

This encyclopedia is organized around a satellite "dictionary". Satellites are sorted alphabetically by name and gathered by space program when possible. Numerous other themes are available such as the countries of origin, the launch vehicles, missions, etc.

The encyclopedia is full of popup windows with technical data and maps.

Search of specific data

The easiest way to find something is to question the searching tool. If your search is unsuccessful either your keyword is unknown or your question wasn't understood: try to ask it differently.

You also can browse through indexes.


 Tag's Broadcasting Services

Ce fichier est un shareware qui appartient à Tag (Jean-Philippe Donnio), © tous droits réservés, 1993-1996.

Ce document fut nommé second meilleur shareware français 1995 catégorie Home and Hobby par Ziff Davis.

A lire également en français :

Licence d'utilisation

Philosophie de cette encyclopédie

Cette encyclopédie a pour but de rassembler de l'information dans un document simple d'emploi. Les contributions sont bien venues.... Vous pouvez même devenir un co-auteur de TSE comme Jean-Jacques Serra qui s'occupe de la section des lanceurs! Cette encyclopédie est publiée tous les 3 mois environ. Ce logiciel n'est donc pas une version finale.

Si vous êtes un spécialiste du satellite, un opérateur ou un constructeur satellite, une organisation spatiale, je serai très heureux d'entrer en contact avec vous. Si pour une raison ou une autre vous pensez que vos satellites ne sont traités correctement, comprenez que je ne travaille qu'avec les informations que j'ai entre les mains. Si vous voulez améliorer les choses, envoyez moi simplement directement vos informations.

Si vous êtes l'auteur d'un livre ou logiciel en rapport avec les satellites ou si votre organisation publie un magazine ou lettre d'information en rapport avec l'Espace et le satellite, consultez mon offre spéciale dans la licence.

Diffusez cette encyclopédie autour de vous : plus elle touchera de monde, plus elle aura de chances de s'enrichir !

La règle du jeu

Ce logiciel est en libre essai, c'est un shareware : vous pouvez donc l'essayer gratuitement pendant SEPT jours, ensuite vous devez soit vous enregistrer soit l'effacer. La version shareware est limitée pour tenir sur une disquette 3,5". De ce fait de nombreuses cartes PIRE et le programme Cosmos ne sont pas inclus. C'est pourquoi vous verrez des erreurs en activant ces éléments.

Si vous utilisez The Satellite's Encyclopedia après la période d'essai ou à des fins commerciales, vous DEVEZ vous enregistrer. La version enregistrée comprend:

Le fichier complet 5.2 Mo avec :

245 cartes PIRE

la liste des satellites sur l'orbite de Clarke

un calendrier des lancements futurs et des satellites concernés

les programmes Russes

TSE est comme un magazine: la version shareware est comparable à un magazine que vous lisez en kiosque. Achetez ce magazine est comme enregistrer votre version de TSE. Et si vous enregistrez TSE avec l'abonnement vous obtenez 4 numeros de TSE consécutifs... ce qui revient à s'abonner à un magazine traditionnel. Bref c'est pas sorcier ! Reportez vous à la licence pour tous les détails.

Dans tous les cas, ce fichier reste ma propriété. Pas de décompilation, merci.

Comment vous procurer la dernière version disponible ?

1°/ En vous enregistrant : voir la licence.

2°/ En la téléchargeant :

Internet : la liste des sites ftp se trouve à http://www.TELE-satellit.com/tse/  Le site ftp primaire se trouve à ftp://ftp.TELE-satellit.com/pub/tse/

3°/ Par l'intermédiaire d'un distributeur de shareware (WindowShare)

Support en ligne

Le site Internet de TSE est http://www.TELE-satellit.com/tse/

La version WWW de TSE se trouve a http://www.TELE-satellit.com/tse/online/

Nous avons mis en place un certain nombre de listes de diffusion. Pour vous abonner (gratuitement) a la liste publique envoyez un mail:

To: majordomo@tags1.dn.net

Subject: none

Body: subscribe tse-pub

Une liste consacrée au developpement de TSE est disponible sous le nom de tse-dev

Contact

Jean-Philippe Donnio

Tag's Broadcasting Services

2 allée des îles

F-14123 Fleury/Orne

France

jpdonnio@tags1.dn.net

SVP : précisez la version de l'encyclopédie dont vous disposez actuellement.

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Pour cela, fournissez :

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Je vous remercierai en vous envoyant la prochaine version de l'encyclopédie.


 Licence d'utilisation

N'hésitez pas à déposer ce logiciel sur des serveurs ou BBS, à faire état de ces capacités et à en donner des copies à des utilisateurs potentiels, pour que d'autres aient la possibilité d'obtenir une copie pour utilisation conformément à la présente licence d'utilisation.

Bon de commande

Bon de commande carte de credit

Licence

L'utilisation de The Satellite's Encyclopedia est soumise aux termes et conditions suivantes :

The Satellite's Encyclopedia est protégée par les lois sur les droits d'auteurs. Vous ne devez faire aucun changement ou modification à The Satellite's Encyclopedia. Vous ne devez pas la décompiler, la désassembler, ou lui appliquer toute autre rétrotechnique. Aucune reproduction autorisée.

Vous pouvez utiliser The Satellite's Encyclopedia pour une période d'essai à condition de ne pas violer la protection que lui procure les lois sur les logiciels, et d'accepter les termes de cette licence. Vous avez le droit d'évaluer gratuitement ce logiciel pendant sept jours. Si vous utilisez The Satellite's Encyclopedia par la suite ou à des FINS COMMERCIALES, vous DEVEZ acquérir une licence d'utilisation. Sinon vous devez effacer le logiciel.

Combien coûte une licence ?

Voir les bons de commande ci-dessus! L'enregistrement donne droit à une version personnelle du logiciel avec :

Le fichier complet 5.2 Mo avec :

245 cartes PIRE

la liste des satellites sur l'orbite de Clarke

un calendrier des lancements futurs et des satellites concernés

les programmes Russes

Un abonnement (4 numéros) est également disponible.

Offre spéciale:

Si vous êtes une société qui publie un périodique papier ou électronique concernant les satellites (en Français, Anglais ou Allemand), vous pouvez obtenir gratuitement une licence d'utilisation avec mise à jour pendant un an contre un abonnement gratuit d'un an à votre publication.

Si vous êtes l'auteur d'un livre concernant les satellites (en Français, Anglais ou Allemand), vous pouvez obtenir gratuitement une licence d'utilisation avec mise à jour pendant 1 an contre un exemplaire gratuit de votre livre.

Si vous êtes l'auteur d'un shareware concernant les satellites (en Français, Anglais ou Allemand), vous pouvez obtenir gratuitement une licence d'utilisation avec mise à jour pendant 1 an contre une licence d'utilisation gratuite de votre shareware.

Je me réserve toutefois le droit de refuser votre demande.

L'utilisateur final ne se voit pas accorder le titre de propriété du logiciel sous licence. On lui fournit une licence non-exclusive pour utiliser, à tous moments, le logiciel sur un unique ordinateur ou station de travail. De plus, il s'engage à ne dupliquer ce logiciel que pour en faire une sauvegarde.

Garantie

Bien que toutes les précautions aient été prises lors de la compilation de ces informations, l'éditeur n'est pas responsable des erreurs ou omissions. De même l'éditeur ne peut être tenu responsable de conséquences de l'utilisation des informations contenues dans cette encyclopédie.

Je ne garantie pas que le logiciel sous licence répondra à vos attentes ou que le logiciel comme les informations seront sans erreurs. La garantie ne couvre aucune copie du logiciel altérée ou modifiée.

Je ne suis pas responsable des problèmes ou dommages causés par le logiciel sous licence qui pourrait résulter de son utilisation. Ceci comprend, mais ne se limite pas au matériel informatique, logiciel informatique, système d'exploitation, et autre accessoire informatique. L'utilisateur final s'engage à me reconnaître irresponsable de problèmes dus à l'utilisation du logiciel.

Je ne serai en aucun cas tenu des dommages-intérêts particuliers, accidentels, conséquents, indirects ou similaires provenant d'une quelconque rupture de ces garanties même si j'ai été prévenu de la possibilité de tels dommages-intérêts.

Ma responsabilité ne pourra en aucun cas excéder le montant de la licence payée en contre partie de l'utilisation du logiciel sous licence.

Dans le cas où quelque disposition de cette licence serait invalide, les parties s'accordent que cette invalidité n'affectera pas la validité du reste des dispositions de cette licence.

Distribution de The Satellite's Encyclopedia

The Satellite's Encyclopedia doit être copiée sans modifications et doit contenir tous les fichiers nécessaires à son installation automatique. Aucune taxe, frais ou autre compensation ne doit être acceptée ou demandée par personne sans mon accord écrit exprès.

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Les opérateurs des serveurs et BBS (les sysops) peuvent mettre The Satellite's Encyclopedia à la disposition de leurs utilisateurs sans permission écrite tant qu'ils respectent les conditions ci-dessus. Une redevance peut être perçue pour accéder au système mais aucune taxe spécifique ne peut être facturée pour le téléchargement des fichiers de The Satellite's Encyclopedia sans l'obtention préalable de mon accord écrit exprès pour facturer une telle somme. Ceci s'applique également à Internet et Compuserve; les autres systèmes en ligne doivent demander une autorisation. En ce qui concerne le Minitel, les fournisseurs de service NE sont PAS autorisés à mettre The Satellite's Encyclopedia en ligne.

Ce qui précède constitue la licence de The Satellite's Encyclopedia. Elle annule et remplace toutes les versions antérieures.


 Jean-Jacques SERRA

Jean-Jacques Serra is a 43 years old French citizen. He devotes most of his free time to astronautics since the age of 17. He is responsible of the launch vehicle section.

He lives in eastern part of the Pyrenees mountains, a region famous for its solar ovens. He carries out research on new materials especially those aimed to extrem temperatures.

Reading of articles and information sorting relative to rockets and satellites consume most of his hobby time. He also enjoys his natural environment.

J'ai 43 ans et je m'intéresse à l'astronautique et son histoire depuis l'age de 17 ans.

Je vis à l'est des Pyrénées, dans une région où se trouve la plus grande concentration de fours solaires. J'y fais de la recherche sur les matériaux nouveaux et plus particulièrement ceux qui sont exposés à des températures extrêmes.

La lecture d'articles, le classement d'informations sur les fusées et les satellites occupent une grande partie de mes loisirs. Pour le reste, je profite de mon environnement, la découverte de la montagne est un sujet inépuisable.


 Gunter Krebs

Gunter is very busy writing his diploma thesis, so he had no time to prepare his presentation. His "biography" will be included in the next release.

Contact

gk@smoky.ikf.physik.uni-frankfurt.de

http://www.rz.uni-frankfurt.de/~gkrebs/space/space.html


 Countries of origin

Statistics (derived from those of NASA Feb 1996)

	Payload in orbit	Debris in orbit	Total in orbit	Payload decayed	Debris decayed	Total decayed
Argentina	1	0	1	0	0	0
Australia	6	2	8	2	1	3
Brazil	6	0	6	0	0	0
Bulgaria	1	1	2	0	0	0
Canada	17	0	17	1	0	1
China	16	94	110	24	83	107
CIS	1345	2514	3859	1647	9777	11424
Czechoslovakia	2	0	2	1	0	1
France	26	19	45	7	59	66
Germany	15	3	18	6	5	11
Hong Kong	1	0	1	0	0	0
India	13	4	17	6	8	14
Indonesia	7	0	7	1	1	2
Israel	1	0	1	2	3	5
Italy	5	0	5	5	0	5
Japan	57	53	110	11	81	92
Korea (South)	4	0	4	0	0	0
Luxemburg	5	2	7	0	0	0
Mexico	4	0	4	0	0	0
Netherlands	0	0	0	1	3	4
Pakistan	0	0	0	1	0	1
Portugal	1	0	1	0	0	0
Spain	4	0	4	0	0	0
Sweden	4	0	4	0	0	0
Thailand	2	0	2	0	0	0
Turkey	1	0	1	0	0	0
United Kingdom	18	1	19	8	4	12
United States	671	2830	3501	671	2908	3578
Arab States	3	0	3	0	0	0
Europe	30	165	195	11	453	474
International	51	0	51	1	0	1
NATO	8	2	10	0	0	0
Column	2325	5690	8015	2406	13386	15792
Total						23807


Countries of origin

Countries

Argentina Australia Brazil Bulgaria Canada CIS Chile China Czechoslovakia France Germany	Hong Kong India Indonesia Israel Italy Japan Korea (South) Luxemburg Malaysia Mexico Netherlands	Norway Pakistan Portugal Spain Sweden Thailand Turkey Ukraine United Kingdom United States
Organizations

Arab States Europe (ESA)	International NATO


 Argentina

Satellite launched

1990

Lusat


 Australia

Australia owns an old launch site (Woomera) from which it's first satellite was launched. Has created a space comity on 21 Sep 1986.

Satellites launched

1967

Wresat

1970

Oscar 05

1985

Optus A1

Optus A2

1987

Optus A3

1992

Optus B1

Optus B2

1994

Optus B3

Main program

Optus


 Brazil

The national space research center INPE (Instituto Nacional de Pesquisas Espacias) was created on 3 Aug 1961.

Satellites launched

1985

Brazilsat A1 (SBTS A1)

1986

Brazilsat A2 (SBTS A2)

1990

Dove

1993

SCD

1994

Brazilsat B1 (SBTS B1)

1995

Brazilsat B2 (SBTS B2)

Main program

Brazilsat


 Bulgaria

Bulgaria launched a satellite with the help of the CIS. Member of Intersputnik.

Satellite launched

1981

Intercosmos Bulgaria 1300


 Canada

The Canadian Space Agency was created on 1 Mar 1989.

Canada is an associate member of ESA since 1978. This means that Canada does not have the same rights and obligations as a full member. For instance, Canada is not participating in the Scientific Program or in the Technological Research Programme of ESA. Both these programs are part of the mandatory activities which are financed by the full members pro rata of their gross national product (GNP).

Canada was the first country to develop a national telecommunication system.

Satellites launched

1962

Alouette 1

1965

Alouette 2

1969

Isis 1

1971

Isis 2

1972

Anik A1 (Telesat 1)

1973

Anik A2 (Telesat 2)

1975

Anik A3 (Telesat 3)

1976

CTS

1978

Anik B1 (Telesat 4)

1982

Anik D1 (Telesat 5)

Anik C3 (Telesat 6)

1983

Anik C2 (Telesat 7)

1984

Anik D2 (Telesat 8)

1985

Anik C1 (Telesat 9)

1991

Anik E2 (Telesat 10)

Anik E1 (Telesat 11)

1992

CTA

1995

Radarsat

Main programs

Alouette

Anik

Isis


 Chile

Satellites launched

1995

Fasat Alfa


 China

In 1958 Mao tze-tung decided to launch a program named "mission 581" directed by Quian Xue-sen. The first Chinese rocket was launched in 1960 (so as the first missile). When the CIS stopped helping China the spatial program changed drastically. Two organizations were created (in Shangai and Beijin) that managed to launch their first satellite. Since 1986 China offers launch services to foreign firms.

Satellites launched

1970

Dong Fang Hong 01 (Mao 1)

1971

Dong Fang Hong 02 (Mao 2)

1975

Dong Fang Hong 03 (Mao 3)

Dong Fang Hong 04 (Mao 4)

Dong Fang Hong 05 (Mao 5)

1976

Dong Fang Hong 06 (Mao 6)

Dong Fang Hong 07 (Mao 7)

1978

Dong Fang Hong 08 (Mao 8)

1981

Dong Fang Hong 09

Dong Fang Hong 10

Dong Fang Hong 11

1982

Dong Fang Hong 12

1983

Dong Fang Hong 13

1984

Dong Fang Hong 14

Dong Fang Hong 15 (STTW 0)

Dong Fang Hong 16

1985

Dong Fang Hong 17

1986

Dong Fang Hong 18 (STTW 1)

Dong Fang Hong 19

1987

Dong Fang Hong 20

Dong Fang Hong 21

1988

Dong Fang Hong 22 (Chinasat 1)

Dong Fang Hong 23

Dong Fang Hong 24(Feng Yun 1-1)

Dong Fang Hong 25 (Chinasat 2)

1990

Dong Fang Hong 26 (Chinasat 3)

Dong Fang Hong 30(Feng Yun 1-2)

Dong Fang Hong 31 (Atmosphere 1)

Dong Fang Hong 32 (Atmosphere 2)

Dong Fang Hong 33

1991

Dong Fang Hong 34 (Chinasat 4)

1992

Dong Fang Hong 35

Dong Fang Hong 36

1993

Dong Fang Hong 37 (Jianbing 93)

1994

Dong Fang Hong 38 (Shijian 4)

Dong Fang Hong 39 (Shijian 4-2)

Dong Fang Hong 40 (FSW 2)

Dong Fang Hong 41

Main programs

Dong Fang Hong


 CIS

For the moment, we name the Russian Federation and the Community of Independant States CIS. All launches by the former USSR are considered as Russian launches. Sorry for this simplification.

CIS has a very complex space organization that we can't simply summarize here.

Main programs

Cosmos

Ekran

Elektron

Eorsat

Express

Foton

Gals

Geizer

Glonass

Gorizont

Intercosmos

Luch

Meteor

Molniya

Nadezhda

Ocean

Prognoz

Proton

Raduga

Resurs

Rorsat

Sputnik

Statsionar

Tsikada

Launchers

Rokot

Start


Czechoslovakia
 Czech Republic

Formerly called Czechoslovakia, before the country splitted.

Developed a scientific program with the CIS. Member of Intersputnik.

Satellites launched

Two of these satellites are not officially registered by the country

1978

Magion 1

1989

Magion 2

1991

Magion 3

1995

Magion 4

Main program

Magion


 France

The French space agency CNES (Centre National d'Etudes Spatiales) was created on 19 Dec 1961. France has been part of ESRO and ELDO. Now it is member of ESA.

Satellites launched

1965

Astérix (A1)

FR 1

1966

Diapason (D1A)

1967

Diadème 1 (D1C)

Diadème 2 (D1D)

1970

Mika

Péole

1971

Tournesol (D2A)

Eole

Auréole 1

1972

Sret 1

1973

Auréole 2

1974

Symphonie 1

1975

Starlette

Pollux (D5A)

Castor (D5B)

Sret 2

Symphonie 2

Aura (D2B)

1977

Signe 3

1981

Auréole 3

1984

Telecom 1A

1985

Telecom 1B

1986

Spot 1

1988

Telecom 1C

TDF 1

1990

Spot 2

TDF 2

1991

Sara

Telecom 2A

1992

Telecom 2B

S80T

1993

Arsène

Spot 3

Stella

1995

Helios 1A

Cerise

Main programs

Argos

Auréole

Helios

Spot

Sret

Symphonie

TDF

Telecom

Launchers

Diamant


 Germany

In the 30ies, a space organization (Verein für Raumschiffahrt, society for space travel) was created with members as famous as Wernher von Braun and H. Oberth. In 1931 they managed to launch a rocket with liquid ergols. During the second world war Germany developed the V2 missile. In 1962 Germany started cooperating with European countries when the COPERS was created.

Germany has been part of ESRO and ELDO. It is now member of ESA. Has created in July 1989 a federal space agency: DARA (Deutsche Agentur für RaumfahrtAngelegenheiten). Member of Intersputnik.

Satellites launched

1969

Azur (GRS A)

1970

Dial-Wika

1972

Aeros 1 (GRS B)

1974

Aeros 2

Symphonie 1

1975

Symphonie 2

1983

Oscar 10

Spas 1

1984

AMPTE IRM

1987

Tvsat 1

1989

DFS 1

Tvsat 2

1990

Rosat

DFS 2

1991

Tubsat A

1992

DFS 3

1993

Orfeus-Spas

1994

Tubsat B

Crista-Spas

1995

GFZ 1

Main programs

Aeros

DFS Kopernikus

Safir

Symphonie

Tubsat

Tvsat


 Hong Kong

Satellites launched

1990

Asiasat 1

1994

Apstar 1

1995

Asiasat 2

Main program

Apstar

Asiasat


 India

Indian space agency is the ISRO (Indian Space Research Organisation) created in 1969. A Ministry of Space was created in 1972 and India has its own launch vehicles.

Satellites launched

1975

Aryabhata

1979

Bhaskara 1

1980

Rohini 1B (RS E2)

1981

Rohini 2 (RS D1)

Apple

Bhaskara 2

1982

Insat 1A

1983

Rohini 3 (RS D2)

Insat 1B

1988

IRS 1A

Insat 1C

1990

Insat 1D

1991

IRS 1B

1992

Sross 3

Insat 2A

1993

Insat 2B

1994

Sross C2

IRS P2

1995

IRS 1C

1996

Insat 2C

IRS P3

Main programs

Bhaskara

Insat

IRS

Rohini

Sross

Launchers

ISRO launch vehicles(SLV 3, ASLV, PSLV)


 Indonesia

Satellites launched

1976

Palapa A1

1977

Palapa A2

1983

Palapa B1

1987

Palapa B2P

1990

Palapa B2R

1992

Palapa B4

1996

Palapa C1

Main program

Palapa


 Israel

Israel has a space agency since 1983

Satellites launched

1988

Offek 1

1990

Offek 2

1995

Offek 3

Main program

Offek


 Italy

Italy is part of ESA and has created a space agency on 8 Jun 1988: ASI (Agenzia Spaziale Italania). Italy owns a little launch site in the Indian ocean (San Marco and Santa Rita).

Satellites launched

1964

San Marco 1

1967

San Marco 2

1971

San Marco 3

1974

San Marco 4

1977

Sirio 1

1988

San Marco 5

1991

Italsat 1

1992

Temisat

1993

Itamsat

1996

TTS 2

Main programs

Italsat

San Marco

Sirio


 Japan

Japan has an important space program conducted by NASDA (National Space Development Agency) and ISAS (Institute of Space and Aeronautical Science).

Satellites launched

1970

Ohsumi

1971

Tansei 1

Shinsei

1972

Denpa

1974

Tansei 2

1975

Taiyo

Kiku 1 (ETS 1)

1976

Ume 1 (ISS 1)

1977

Tansei 3

Kiku 2 (ETS 2)

Himawari 1 (GMS 1)

Sakura 1 (CS 1A)

1978

Kyokko (Exos A)

Ume 2 (ISS 2)

Yuri 1 (BSE)

Jikiken (Exos B)

1979

Ayame 1 (ECS 1)

Hakucho (Corsa B)

1980

Tansei 4

Ayame 2 (ECS 2)

1981

Kiku 3 (ETS 4)

Hinotori (Astro A)

Himawari 2 (GMS 2)

1982

Kiku 4 (ETS 3)

1983

Sakura 2A (CS 2A)

Tenma (Astro B)

Sakura 2B (CS 2B)

1984

Yuri 2A (BS 2A)

Ohzora (Exos C)

Himawari 3 (GMS 3)

1986

Yuri 2B (BS 2B)

Ajisai (EGP)

Fuji 1A (JAS 1A)

1987

Ginga (Astro C)

Momo 1A (MOS 1A)

ETS 5

1988

Sakura 3A (CS 3A)

Sakura 3B (CS 3B)

1989

Akebono (Exos D)

Jcsat 1

Superbird A1

Himawari 4 (GMS 4)

1990

Jcsat 2

Hiten (Muses A) & Hagoromo: lunar probes

Momo 1B (MOS 1B)

Debut

Fuji 1B (JAS 1B)

Yuri 3A (BS 3A)

1991

Yuri 3B (BS 3B)

Solar A (Yohkoh)

1992

JERS 1

Superbird B1

Geotail

Superbird A2

1993

Astro D

1994

Ryusei

Myojo

Yuri 3N

1995

SFU

GMS 5

Jcsat 3

N Star A

Main programs

Astro

Ayame

ETS

Fuji

GMS

Jcsat

Momo

Sakura

Superbird

Tansei

Yuri

Launchers

ISAS launch vehicles (Mu series)

H2


 Korea (South)

Satellites launched

1992

Kitsat A

1993

Kitsat B

1995

Koreasat 1

1996

Koreasat 2

Main programs

Kitsat

Koreasat


 Luxemburg

Satellites launched

1988

Astra 1A

1991

Astra 1B

1993

Astra 1C

1994

Astra 1D

1995

Astra 1E

Main program

Astra


 Malaysia

Malaysia plans to launch a micro satellite in the middle of 1997 (on Ariane) and the second in 2000

Satellite launched

1996

Measat 1

Main program

Measat


 Mexico

Satellites launched

1985

Morelos 1

Morelos 2

1993

Solidaridad 1

1994

Solidaridad 2

Main programs

Morelos

Solidaridad


 Netherlands

Member of ESA

Satellites launched

1974

ANS

1974

IRAS


 Norway

Member of ESA since 1987.

Satellite bought in orbit

1992

Thor


 Pakistan

Satellite launched

1990

Badr A


 Portugal

Satellite launched

1993

Posat


 Spain

Spain is part of ESA.

Satellites launched

1974

Intasat

1992

Hispasat 1A

1993

Hispasat 1B

1995

UPMsat 1

Main program

Hispasat


 Sweden

Member of ESA

Satellites launched

1986

Viking

1989

Tele X

1992

Freja

1994

Sirius 1 (bought in orbit)

1995

Astrid


 Thailand

Satellite launched

1993

Thaicom 1

1994

Thaicom 2

Main program

Thaicom


 Turkey

Satellite launched

1994

Turksat 1B

Main program

Turksat


 Ukraine

Ukraine has a space agency: National Space Agency of Ukraine (NKAU)

Satellites launched

1995

Sich 1


 United Kingdom

Has created the BNSC (British National Space Center), a space agency in 1985. United Kingdom is member of ESA.

Satellites

1962

Ariel 1 (UK 1)

1964

Ariel 2 (UK 2)

1967

Ariel 3 (UK 3)

1969

Skynet 1A

1971

Skynet 1B

Prospero (X3)

Ariel 4 (UK 4)

1974

Skynet 2A

Miranda (X 4)

Ariel 5 (UK 5)

Skynet 2B

1979

Ariel 6 (UK 6)

1981

Uosat 1

1983

IRAS

1984

Uosat 2

AMPTE UKS

1988

Skynet 4B

1989

BSB 1

Skynet 4A

1990

Uosat 3

Uosat 4

BSB 2

Skynet 4C

1991

Uosat 5

1994

STRV 1A

STRV 1B

Main programs

Ariel

BSB

Skynet

STRV

Uosat

Launchers

Black Arrow


 United States

The US space program can't be described here...

Main programs

AMS

AMSC

Argos

ASC

ATS

Aurora

Comstar

Dash

DBS

Discoverer

DMSP

DSCS

DSP

Echo

Echostar

Essa

Explorer

Fleetsatcom

Galaxy

GGSE

Goes

GPS

Gstar

Heao

IDSCP

IMEWS

KH

Lacrosse

Lageos

Landsat

LCS

Leasat

LES

Marisat

Midas

Nimbus

NOAA

NOSS

Nova

OAO

Oderacs

OGO

Orbcomm

Orion

OSO

OV

Panamsat

Pegasus

Relay

Satcom

Discoverer

SBS

Secor

SMS

Solrad

Spacenet

Spartan

Syncom

TDRS

Telstar

Tiros

Transit

UHF

USA

Vanguard

Vortex

Westar

Launchers

Atlas

Conestoga

Delta

LLV

Pegasus

Scout

STS

Taurus

Thor

Titan 4


 Arab States

Satellites launched

1985

Arabsat 1A

Arabsat 1B

1992

Arabsat 1C

1993

Arabsat 1D (bought in orbit)

Main program

Arabsat


 Europe

We use the name 'Europe' to simplify naming. In fact, it may stand for the ESA or the ESRO.

On 27 Feb 1961 the COPERS (COmmission Préparatoire Européenne pour la Recherche Spatiale) was created. In 1964 the ESRO (European Space Research Organization) was created to develop satellites. The ELDO (European Launcher Development Organisation) was in charge of the development of the Europa launcher. The Convention establishing this organisation came into force on 29 February 1964. This multiple structure merged into a single organization ESA (European Space Agency) on 31 May 1975.

Members of ESA: Austria, Belgium, Denmark, Finland, France, Germany, Ireland, Italy, Netherlands, Norway, Spain, Sweden, United Kingdom, and Switzerland. Canada is an associate member.

The convention says: the purpose of the agency shall be to provide for and to promote, for exclusively peaceful purposes, cooperation among European states in space research and technology and their space applications, with a view to their being used for scientific purposes and for operating space applications systems.

The agency is directed by a council composed of representatives of member states. The Director General is the chief executive of the agency and its legal representative. The ESA headquarters are in Paris.

The major establishments of ESA are: The European Space Research and Technology Center (ESTEC), Noordwijk, Netherlands; The European Space Operations Center (ESOC), Darmstadt, Germany; ESRIN, Fracasti, Italy.

Contact

ESA

8/10 rue Mario Nikis, 75738 Paris cedex 15, France

Tel: +33-1-4273-7560

Satellites launched

1968

Esro 2B (Iris)

Esro 1A (Aurorae)

Heos 1

1969

Esro 1B (Boreas)

1972

Heos 2

TD 1A

Esro 4

1975

Cos B

1977

ESA-Geos 1

ISEE 2

Meteosat 1

1978

OTS 2

ESA-Geos 2

1979

Cat 1

1981

Meteosat 2

Cat 3

Marecs A

Cat 4

1983

Exosat

Eutelsat 1F1

1984

Eutelsat 1F2

Marecs B2

1987

Eutelsat 1F4

1988

Meteosat 3

Eutelsat 1F5

1989

Meteosat 4

Olympus

Hipparcos

1990

Eutelsat 2F1

1991

Eutelsat 2F2

Meteosat 5

ERS 1

Eutelsat 2F3

1992

Eutelsat 2F4

Eureca 1

1993

Meteosat 6

1995

Hotbird 1

ERS 2

ISO

Soho

Main programs

Cat

Esro

ERS

Eutelsat

Heos

Marecs

Meteosat

OTS

Launchers

Ariane


 International

Here are the satellites developed by an international organization, either Intelsat or Inmarsat. Intersputnik isn't in here because the satellites are owned by the CIS... but this will change as soon as Intersputnik launches its first satellite.

Numerous other programs were developed by multi-national partners but are still considered nationally.

Satellites launched

1965

Intelsat 101

1966

Intelsat 201

1967

Intelsat 202

Intelsat 203

Intelsat 204

1968

Intelsat 302

1969

Intelsat 303

Intelsat 304

1970

Intelsat 306

Intelsat 307

Intelsat 308

1971

Intelsat 402

Intelsat 403

1972

Intelsat 404

Intelsat 405

1973

Intelsat 407

1974

Intelsat 408

1975

Intelsat 401

Intelsat 4A01

1976

Intelsat 4A02

1977

Intelsat 4A04

1978

Intelsat 4A03

Intelsat 4A06

1980

Intelsat 502

1981

Intelsat 501

Intelsat 503

1982

Intelsat 504

Intelsat 505

1983

Intelsat 506

Intelsat 507

1984

Intelsat 508

Intelsat 509

1985

Intelsat 510

Intelsat 511

Intelsat 512

1988

Intelsat 513

1989

Intelsat 515

Intelsat 602

1990

Intelsat 603

Intelsat 604

Inmarsat 2F1

1991

Inmarsat 2F2

Intelsat 605

Intelsat 601

Inmarsat 2F3

1992

Inmarsat 2F4

Intelsat K

1993

Intelsat 701

1994

Intelsat 702

Intelsat 703

1995

Intelsat 704

Intelsat 705

Intelsat 706

1996

Intelsat 707

Main programs

Inmarsat

Intelsat

ISEE

Sarsat


 NATO

Satellites launched

1970

Nato 1

1971

Nato 2

1976

Nato 3A

1977

Nato 3B

1978

Nato 3C

1984

Nato 3D

1991

Nato 4A

1993

Nato 4B

Main program

Nato


 The Clarke Belt

This chart keeps track of the satellites on the Clarke Belt.

First column is the slot of the satellite above the Equator; negative values stand for degrees West and positive for degrees East. Second column is the inclination of the spacecraft in degrees i.e. the angle between the satellite's plan anf the Equator's plan. The "Mis." column is for the satellite's main mission; M stands for Military, C for Communication and W for Weather. Furthermore MC stands for Military Communications, MW for Military Warning. The "Frequency bands" column relates the downlink bands in which the satellite can be active, blank means unknown. The "Comment" column contains internal information, such as the "!" sign which indicates this data is unconfirmed or variable.

Slot	Inc.	Satellite	Mis.	Freq. bands	Comment
-178.0	4.73	UHF 4	M	UHF, X, EHF
-178.0	12.9	Marisat 3	C	L, C
-177	6.24	Leasat 2	M	UHF, X	wavering
-177.0	0.46	Intelsat 513	C	C, Ku
-176	12.2	Goes 2	C	S	!wavering but alive
-174.3	0.05	TDRS 5	M	S, C, Ku
-170.0	5.77	Raduga 21	C/M	C, X
-150.0	0.53	TDRS 7	M	S, C, Ku	reserve
-139.0	0.05	Aurora 2	C	C
-137.0	0.05	Satcom C1	C	C
-135.0	0.09	Goes 9	W	VHF, L, S	wavering
-135.0	0.05	Satcom C4	C	C
-133.0	0.03	Galaxy 1R	C	C
-131.0	0.05	Satcom C3	C	C
-130.0	5.04	DSCS 3-01	M	X
-125.0	0.03	Galaxy 5	C	C
-124.9	0.83	Gstar 2	C	Ku
-123.0	0.70	Telstar 303	C	C
-122.9	0.03	SBS 5	C	Ku
-120		USA 099	M	UHF, Ka, EHF
-119.0	0.03	Echostar 1	C	Ku
-116.8	0.05	Morelos 2	C	C, Ku
-114.9	3.84	Anik C3	C	Ku
-114	2.91	Goes 7	W	VHF, L, S	!drifting East
-113.0	0.03	Solidaridad 2	C	L, C, Ku
-111.1	0.03	Anik E1	C	C, Ku
-109.2	0.03	Solidaridad 1	C	L, C, Ku
-107.3	0.03	Anik E2	C	C, Ku
-106.7	4.90	UHF 6	M	UHF, X, EHF
-106.0	5.65	Leasat 3	M	UHF, X
-106.0	12.3	Marisat 1	C	L, C
-105	15.4	LES 9	M		!old
-105	14.9	ATS 3	C	VHF,	!old
-105.5	4.16	Aurora 1	C	C
-105.0	0.03	Gstar 4	C	Ku
-105.4	15.3	LES 8	M		!old, drifting West
-103.0	0.08	Gstar 1	C	Ku
-101.2	0.03	DBS 1	C	Ku
-101.0	0.05	ASC 2	C	C, Ku
-101.0	0.05	AMSC 1	C	L, Ku
-101.0	0.03	DBS 3	C	Ku
-100.8	0.03	DBS 2	C	Ku
-100.0	0.05	ACTS	C	Ka
-99.7	2.72	Fleetsatcom 7	M	UHF, X	wavering
-99.0	0.03	Galaxy 4	C	C, Ku
-97.0	0.03	Telstar 401	C	C, Ku
-95.0	0.03	Galaxy 3R	C	C, Ku
-93.0	7.18	Gstar 3	C	Ku
-92.0	0.07	Brazilsat A2	C	C
-91.0	0.03	Galaxy 7	C	C, Ku
-89.0	0.03	Telstar 402R	C	C, Ku
-87.0	0.05	Spacenet 3R	C	L, C, Ku
-85.1	0.97	Telstar 302	C	C
-85.0	0.03	Satcom K1	C	Ku
-80.9	0.03	Satcom K2	C	Ku
-77.0	2.55	SBS 4	C	Ku
-76.0	8.73	Comstar 4	C	C
-75.9	3.72	Anik C2	C	Ku
-75.0	0.13	Goes 8	W	VHF, L, S	wavering
-74	8.85	TDRS 1	M	S, C, Ku	!drifting East to 49°W
-74.1	0.05	SBS 6	C	Ku
-74.0	0.05	Galaxy 6	C	C
-71.8	0.03	Anik C1	C	Ku
-71.0	6.85	SBS 2	C	Ku
-70.0	0.03	Brazilsat B1	C	C, X
-69.0	0.05	Spacenet 2	C	C, Ku
-65.0	0.03	Brazilsat B2	C	C, X
-63.0	1.22	Brazilsat A1	C	C
-54.0	2.68	Inmarsat 2F4	C	L, C
-53.0	0.03	Intelsat 706	C	C, Ku
-52		DSCS 3-05	M	P, C
-50.0	0.03	Intelsat 705	C	C, Ku
-46.0	2.45	TDRS 6	M	S, C, Ku	reserve
-45.0	0.05	Panamsat 1	C	C, Ku
-45		DSCS 3-03	M	P, C
-43.0	0.03	Panamsat 3R	C	C, Ku
-41.0	0.07	TDRS 4	M	S, C, Ku
-40.3	6.23	Intelsat 502	C	C, Ku
-37.5	0.05	Orion 1	C	Ku
-34.5	0.03	Intelsat 603	C	C, Ku
-34.0	2.33	Skynet 4A	M	UHF, X, EHF
-31	1.15	Cosmos 2282	MW	S	!drifting west
-31.4	4.37	Intelsat 506	C	L, C, Ku
-30.0	0.05	Hispasat 1A	C	X, Ku
-30.0	0.05	Hispasat 1B	C	X, Ku
-27.5	0.03	Intelsat 601	C	C, Ku
-24.5	0.03	Intelsat 605	C	C, Ku
-24.0	1.47	Cosmos 2209	MW	S	wavering
-23.0	1.98	Fleetsatcom 8	M	UHF, X
-21.5	0.05	Intelsat K	C	Ku
-21.3	1.70	Intelsat 512	C	C, Ku
-21.0	3.83	Nato 3D	M	X
-18.8	0.09	TDF 2	C	Ku
-18.8	0.09	TDF 1	C	Ku
-18.0	0.05	Intelsat 515	C	C, Ku
-18.0	2.08	Nato 4A	M	UHF, X
-16.0	3.70	Cosmos 2054	MC	UHF, Ku
-15.8	2.14	Inmarsat 2F2	C	L, C
-15.5	4.35	UHF 3	M	UHF, X
-15	12.7	Fleetsatcom 1	M	UHF, X
-15.0	6.04	Marecs B2	C	L, C
-14.2	2.09	Cosmos 2172	MC	C
-14.0	0.10	Express 01	C	C, Ku
-13.5	0.35	Cosmos 2291	MC	C
-12		DSCS 3-06	M	P, C
-11.5	1.46	Gorizont 26	C	L, C, Ku	wavering
-10	0.23	Meteosat 6	W	VHF, L, S
-9	3.2	Telecom 1C	C/M	C, X, Ku	!no recent elements available
-8.0	0.05	Telecom 2A	C/M	C, X, Ku
-5.0	0.03	Telecom 2B	C/M	C, X, Ku
-1.0	1.05	Skynet 4C	M	UHF, X, EHF
-1.0	0.03	Intelsat 702	C	C, Ku
-0.8	0.07	Thor	C	Ku
-0.6	0.16	Tvsat 2	C	Ku
0	0.39	Meteosat 5	W	VHF, L, S	wavering
1	0.10	Intelsat 707	C	C, Ku	new
3.0	0.03	Telecom 2C	C/M	C, X, Ku
4		USA 115	M	UHF, Ka, EHF
5.0	0.07	TELE X	C	Ku
5.2	0.05	Sirius 1	C	Ku
5.5	2.94	Nato 4B	M	UHF, X
7.0	0.03	Eutelsat 2F4	C	Ku
10.0	0.05	Eutelsat 2F2	C	Ku
12.0	0.90	Raduga 29	MC	C, X
12.0	4.77	Raduga 22	MC	C, X
12.0	0.63	Cosmos 2224	MW	S
13.0	0.05	Hotbird 1	C	Ku
13.0	0.05	Eutelsat 2F1	C	Ku
13.2	0.05	Italsat 1	C	Ka
16.0	0.03	Eutelsat 2F3	C	Ku
19.2	0.07	Astra 1A	C	Ku
19.2	0.07	Astra 1B	C	Ku
19.2	0.07	Astra 1C	C	Ku
19.2	0.05	Astra 1D	C	Ku
19.2	0.03	Astra 1E	C	Ku
20.0	1.95	Telstar 301	C	C
21.5	1.55	Eutelsat 1F5	C	Ku
22.5	7.82	Marecs A	C	L, C
23.5	0.05	DFS 3	C	Ku, Ka
25.5	2.37	Eutelsat 1F4	C	Ku
26.0	3.30	Gorizont 20	C	L, C, Ku
28.5	0.05	DFS 2	C	Ku, Ka
31.0	0.05	Arabsat 1C	C	S, C
34.0	4.57	Gorizont 17	C	L, C, Ku
35.0	1.98	Raduga 28	MC	C, X
36	5.51	Eutelsat 1F1	C	Ku	drifting West
40.0	1.37	Gorizont 31	C	L, C, Ku
42.0	0.05	Turksat 1B	C	Ku
45.0	4.36	Raduga 23	MC	C, X
47.0	4.75	Intelsat 507	C	L, C, Ku
49.0	2.82	Raduga 1-2	MC	C, X
49.0	0.19	Raduga 1-3	MC	C, X
53.0	3.20	Skynet 4B	M	UHF, X, EHF	wavering
53.0	1.06	Gorizont 27	C	L, C, Ku
57.0	2.99	Intelsat 510	C	C, Ku
60.0	0.03	Intelsat 604	C	C, Ku
60		DSCS 3-02	M	P, C
60	2.85	Raduga 26	MC	C, X	!drifting West
62.9	0.03	Intelsat 602	C	C, Ku
64.3	1.75	Inmarsat 2F1	C	L, C
64.9	5.36	Intelsat 505	C	L, C, Ku
65.0	8.09	DSCS 2-15	M	C	wavering
66.0	0.03	Intelsat 704	C	C, Ku
68.5	0.05	Panamsat 4	C	C, Ku
70.0	4.20	Raduga 1-1	MC	C, X
70.0	0.54	Raduga 32	MC	C, X
71.0	0.06	Gals 1	C	Ku
71.0	0.06	Gals 2	C	Ku
71.5	4.18	UHF 2	M	UHF, X
71.5	4.75	UHF 5	M	UHF, X, EHF
71.5	3.37	Leasat 5	M	P, X
72.0	6.76	Intelsat 501	C	C, Ku
72.5	11.5	Marisat 2	C	P, L, C
72	1.74	Cosmos 2133	MW	S	!drifting West
73	3.21	Cosmos 2085	MC	C	!drifting East
74.0	0.05	Insat 2A	C/W	S, C
76.0	0.19	Electro 1	W	L
76.8	2.68	Luch 1	MC	UHF, Ku
78.5	0.03	Thaicom 1	C	C, Ku
78.5	0.03	Thaicom 2	C	C, Ku
79.8	1.08	Cosmos 2319	MC	C
80.0	2.13	Gorizont 24	C	L, C, Ku
83.0	0.03	Raduga 31	MC	C, X
83.0	0.05	Insat 1D	C/W	S, C
85.0	0.51	Raduga 30	MC	C, X	wavering
85.0	2.35	TDRS 3	M	S, C, Ku	wavering
87.5	2.37	Dong Fang Hong 22	C	C	wavering
90.0	0.47	Gorizont 28	C	L, C, Ku
91.5	0.05	Measat 1	C	C, Ku
93.5	0.03	Insat 2C	C/W	S, C
93.5	0.05	Insat 2B	C/W	S, C
95.0	1.58	Luch 0	MC	UHF, Ku
96.5	3.99	Gorizont 19	C	L, C, Ku
98.0	0.57	Dong Fang Hong 26	C	C
99.0	4.75	Ekran 19	C	UHF
99.0	1.20	Ekran 20	C	UHF
100.5	0.03	Asiasat 2	C	C, Ku
103.0	1.76	Gorizont 25	C	L, C, Ku
105.5	0.05	Asiasat 1	C	C
108.0	0.05	Palapa B2R	C	C
109.7	0.05	Yuri 3N	C	Ku
110.0	0.05	Yuri 3A	C	Ku
110.0	0.03	Yuri 3B	C	Ku
110.5	0.79	Dong Fang Hong 25	C	C
113.0	0.15	Palapa B2P	C	C
113.1	0.05	Palapa C1	C	C, Ku
115.5	0.05	Spacenet 1	C	C, Ku
116.0	0.05	Koreasat 1	C	Ku
116.0	0.05	Koreasat 2	C	Ku
118.0	0.05	Palapa B4	C	C
120.0	1.64	GMS 4	W	UHF, L, S
128.0	0.03	Jcsat 3	C	C, Ku
128.0	2.89	Raduga 27	MC	C, X
130.0	0.44	Gorizont 29	C	C, Ku
131.9	0.03	Sakura 3A	C	C, Ka
132.0	0.03	N Star A	C	S, C, Ku, Ka
134	2.94	Gorizont 22	C	L, C, Ku	!drifting East
136.0	0.03	N Star B	C	S, C, Ku, Ka
136.1	0.03	Sakura 3B	C	C, Ka
138.0	0.03	Apstar 1	C	C
140.0	0.47	GMS 5	W	UHF, L, S
140.0	4.11	Gorizont 18	C	L, C, Ku
142.5	0.20	Gorizont 30	C	C, Ku
145.0	3.02	Gorizont 21	C	L, C, Ku
150.0	0.03	Jcsat 1	C	Ku
150.3	3.88	ETS 5	C	L, C
152.0	0.48	Optus A3	C	Ku
154.0	0.03	Jcsat 2	C	Ku
156.0	0.05	Optus B3	C	L, Ku
157.0	5.87	Intelsat 503	C	C, Ku
158.0	0.05	Superbird A2	C	X, Ku, Ka
160.0	0.03	Optus B1	C	L, Ku
162.0	0.05	Superbird B1	C	X, Ku, Ka
164.0	2.31	Optus A2	C	Ku
169.0	0.03	Panamsat 2	C	C, Ku
172.0	10.6	Fleetsatcom 4	M	UHF, X
174.0	0.03	Intelsat 701	C	C, Ku
177.0	0.03	Intelsat 703	C	C, Ku
178.0	0.46	Inmarsat 2F3	C	L, C
180.0	2.57	Intelsat 511	C	C, Ku


 To be launched

Late, to be rescheduled

*??	COMET (Conestoga)
??	Coupon 1
*??	Coupon 2
*??	Coupon 3
*??	Faisat-Coscon (Russian launcher, Plesetsk)
*??	P91-1/Argos (Delta 2)
*??	SMEX 06
*??	SSTP
March 1996

??	DSP F18 (titan 4)
??	Faisat 2 + Tubsat 2 (Cosmos 3M?, Plesetsk)
April 1996

01	Inmarsat 3F2 (Atlas 2A AC124)
09	Titan 4 Centaur classified launch
10	Apstar 1A (Long March 3)
12	Astra 1F (Proton)
12	Sunsat
18	MSX (Delta 2)
19	MSTI 3 (Pegasus XL)
23	AMSC 2 (Ariane 42P) or MSAT 1 (for Telesat Mobile Inc.)
30	SAX (Atlas 1 AC078)
May 1996

08	Galaxy 9 (Delta 2 7925)
15	Amos 1 ? (Ariane) Palapa C2
16	STS 77
23	GE 2 (Atlas 2A AC123)
late	Cluster (ESA/NASA, Ariane 5)
??	DFH (Long March) (GEO telecom bird to replace the failed DFH 41)
??	Express 2 (Proton)
Jun 1996

01	TOMS (Pegasus XL)
27	STS 78
30	GPS BIIA (Delta 2)
??	Clark (LLV #2) NASA, built by CTA Inc
??	Italsat 2 (Ariane 44L) Inmarsat 3F3
??	SMEX 07
??	Tempo 1 (Proton)
Jul 1996

15	FAST (Fast Auroral Snapshot) (Pegasus XL)
18	UHF 7 (Atlas 2 AC125)
*??	Chinasat 7 (Long March 3) built by Hughes and to be operated by Chinasat (China Satellite Telecommunications) a company under the control of the Ministry of Post and Telecommunications (MPT) equipped with 24 C-band transponders, based on the HS-376 platform, for China and the South China Sea area
*??	Inmarsat 3F1 (Atlas 2A AC124)
??	Inmarsat 3F4 (Proton)
*??	Iridium 1 & 2 (Long March 2C)
??	Lewis (NASA, built by TRW, LLV #3)
??	Intelsat 709 (Ariane 44LP)
Aug 1996

01	NOAA K (titan 2)
01	STS 79
07	Hotbird 2 (Atlas 2A AC129)
28	GPS (Delta 2)
??	ADEOS/NSCAT (H2)
??	GE 1 (Ariane 44L)
??	Turksat 1C (Ariane 44LP) Arabsat 2A
Sep 1996

18	Loral DBS (Atlas 2AS AC128)
??	ARD (Ariane 502)
??	Echostar 2 (Ariane 4)
Oct 1996

15	SWAS (Pegasus XL)
??	Intelsat 801 (Ariane 44LP)
??	Measat 2 (Ariane) Nahuel 1
Nov 1996

07	STS 80
??	DSCS (Atlas 2 AC109)
??	Geosat (Taurus)
Dec 1996

05	STS 81
15	HETE (Pegasus XL) SAC B (Argentine)
??	Iridium #? (Proton)
??	Thaicom 3 (Ariane)
??	UHF 8 (Atlas 2 AC131)
1996

??	Apstar 2R (Long March 3B)
??	Arabsat 2B
??	DBS 4 (Ariane? unconfirmed)
??	Goes K
??	Insat 2D (Ariane)
??	Minisat 1 (remote sensing bird based on the UOSAT bus) (rokot)
??	Panamsat 5
??	Pansat
??	Prognoz 12 + Fasat Bravo + Magion 5 (Molniya M, Plesetsk)
??	Sich 2 (Cyclone 3 or Zenit 2)
?	5 titans planned
Jan 1997

15	Seastar (Pegasus XL)
??	Helios 1B (Ariane)
??	Intelsat 802 (Ariane 44LP)
1997

early	Hotbird 3 (Ariane)
early	Mabuhay (Long March 3C)
early	rokot launch (Plesetsk)
early	SCD 2 (first launch of the VLS, Brazilian launcher)
Jan	Jcsat 4 (Atlas 2AS)
Feb	Indostar 1 (Ariane)
Feb	Thor 2A (Delta 2)
Apr	BSat 1A (Ariane)
Apr	DSCS (Atlas 2)
Apr	Intelsat 803 (Ariane 44LP)
Apr	UHF 9 (Atlas 2)
May	DSCS (Atlas 2)
Jun	Meteosat 7 (Ariane)
Jun	Phase 3D (Ariane 4, secondary payload)
Jun	Sinosat (Long March 3C)
Jul	Globalstar (Delta 2 7925)
Jul	Intelsat 804
Jul	Superbird C (Atlas 2AS)
mid	Comets 1 (Japan experimental comsat)
mid	Telstar 5
Aug	UHF 10 (Atlas 2)
Aug	Intelsat 805 (Atlas 2AS)
Oct	CBERS 1 (Long March 4 or 2C)
Oct	Echostar 3 (Long March 3B)
fall	MCI-News Corp DBS satellite system at 110°W
Nov	Chinastar 1 (Long March 3)
Nov	Skynet 4D (Delta 2 7925)
Dec	DSCS (Atlas 2)
Dec	Intelsat 806 (Atlas 2AS)
late	Agrani 1
late	Asiasat 3 (Proton)
late	Brazilsat B3 (Ariane)
late	Hotbird 4 (Ariane)
late	Insat 2E (Ariane)
late	MCI 1
late	Nilesat 1 (Ariane)
late	Panamsat 7 (Ariane)
??	Agila 1 (PASI 1) (Ariane unconfirmed)
??	Astra 1G
??	DBSC 1
??	Gals 3
??	Gals R12
??	Orbcomm 4 launches scheduled on Pegasus XL
??	Panamsat 8 (Proton?)
??	Program: Yamal (Russian vehicle)
??	Safir 1
??	Sirius 2 (Ariane)
??	Spot 4 (Ariane)
??	Step 4 (Pegasus)
??	VSOP (Japan, Mu 5)
?	Aerospatiale SA said it has received a contract to build a satellite communications system for China. It contract is for two communications satellites, the first to be delivered in early 1997???
1998

early	Agrani 2
early	L Star 1
early	MCI 2
Mar	Eutelsat 3F1 (Ariane)
Apr	Rocsat 1 (taiwan, LLV, scientific experiments)
May	Eutelsat 3 SESAT (Proton)
May	Landsat 7 (Delta 2)
mid	Afristar (Ariane)
mid	L Star 2
Sep	Eutelsat 3F2 (Ariane)
late	Asiastar (Ariane)
late	Intersputnik 8
??	12 Globalstars (Long March 2E)
??	Amos 2
??	APMT
??	Astra 1H
??	BSat 1B (Ariane)
??	EOS AM
??	Galaxy 8I
??	Gals 4
??	Inmarsat 3F5 (Ariane)
??	IRS 1D (PSLV)
??	Odyssey (Atlas 2AS)
??	Orion 2 (Atlas)
??	Singapore and Taiwan intend to launch a telecom satellite in 1998 (made by Hughes, 24 transponders, cost: $300 million paid 50-50 by the two countries)
??	Skynet 4E (Ariane)
??	Spaceway (Delta 3?)
??	Telecom 2D (Ariane)
??	Thai company Asia Broadcasting and Communication Network (ABCN); owned by Sondhi Limthongkul, has announced it has concluded an agreement with the Laos government to build a communication satellite. The agreement will allow Sondhi to operate the satellite under a 30-year concession [<g>]. The satellite will have 12 transponders, two of which will be taken by the laos government, leaving 10 for Sondhi's compagnies. Eight of these Sondhi plans to lease to other players. A number of manufacturers, among them Hughes, Lockheed Martin, Loral and Aerospatiale have been asked to tender to build the satellite. At a cost of $150 million to $200 million, it is expected to be launched within two years. [=1998]
1999

Apr	Eutelsat 3F3
mid	Caribstar (Ariane)
mid	Intersputnik 8
??	Astro E (Mu 5)
??	CBERS 2 (Long March)
??	DRS (ESA, Ariane)
??	Galaxy 10 (delta 3?)
??	IRS 2A (PSLV)
??	MTsat (H2)
??	Orion 4
??	Telstar 6
??	Turksat 1D
??	XMM (ESA, Ariane)
2000

??	EOS PM-1
??	MSG 1 (Ariane 5)
??	Telstar 7
??	Vietnam plans to launch a GEO telecom satellite with 15-20 years ligfetime estimated to cost 250-300 million USD It would be operated by the Vietnam Post and Telecommunications (VNPT)
2001

??	Integral (ESA)
2002

??	EOS Chemistry 1
??	MSG 2 (Ariane 5, unofficial)
2003

??	Rosetta (ESA)
2006

??	MSG 3 (Ariane 5, unofficial)
No date

??	Elekon
??	Ellipsat
??	GE*Star
??	NOAA L (titan 2)
??	NOAA M (titan 2)
??	Orion 3
??	Skynet 4F
??	Simon Bolivar
??	Thurayya
??	Oct 1995: List of FCC bidders for satellite and bandwidth allocation: Loral Corp. Teledesic Corp. Hughes Electronics Corp. as many as 15 HS 702 to expand its nine-satellite Galaxy fleet PanAmSat, two satellites on C and Ku bands and two satellites on the Ka band Lockheed Martin Corp., - nine-satellite system = Astrolink Motorola - four-satellite system called Millenium GE American Communications Inc. - nine-satellite system  Echostar Satellite Corp.-  two additional satellites  NetSat 28 LLC - one satellite AT&T Corp. up to 12 satellites


 Glossary

Apogee	The orbital point were the satellite is furthest from the earth

Apogee Kick Motor	A motor on board the satellite that enables the satellite to move from GTO to GEO

Bandwidth	Range on frequency the transponder can transmit, in MHz

BOL	Begin Of Life

Catalog number	The number that identifies a satellite, attributed by NASA. See CATNR

Clarke belt	The geostationary orbit, named after Arthur Clarke that first said that such an orbit should exist

COMINT	Communication Intelligence

CONUS	Continental United States

Coverage	Zone where the satellite's signals can be received

DC power	Total power produced by the solar panels or nuclear reactor

DCME	Digital Circuit Multiplication Equipment

DCP	Data Collection Platform

Downlink	The satellite to earth signal path

EIRP	Effective Isotropic Radiated Power
Technical value that evaluates the strength of the signals

ELINT	Electronic Intelligence

EOL	End Of Life

Footprint	A zone covered by a satellite's signals

Frequencies (GHz if not specified)

HF-band	1.8 - 30 MHz
VHF-band	50 - 146 MHz
P-band	0.230 - 1.000 GHz
UHF-band	430 - 1300 MHz
L-band	1.530 - 2.700
FCC's digital radio	2.310 - 2.360
S-band	2.700 - 3.500
C-band	Downlink: 3.700 - 4.200 Uplink: 5.925 - 6.425 Standard US chart (horizontal) Standard US chart (vertical)
X-band	Downlink: 7.250 - 7.745 Uplink: 7.900 - 8.395
Ku-band (Europe)	Downlink: FSS: 10.700 - 11.700 DBS: 11.700 - 12.500 Telecom: 12.500 - 12.750 Uplink: FSS & Telecom: 14.000 - 14.800 DBS: 17.300 - 18.100
Ku-band (America)	Downlink: FSS: 11.700 - 12.200 DBS: 12.200 - 12.700 Uplink: FSS: 14.000 - 14.500 DBS: 17.300 - 17.800

GEO	Geostationary Earth Orbit

Geostationary orbit	The circular orbit at 35.780 km above the equator. Satellites slotted on this orbit always appear at the same position in the sky. In degrees towards East (E or positive) or West (W or negative) from the Greenwich meridian.

GTO	Geostationary Transfer Orbit
Geostationary satellites are usually launched on a temporary orbit before being moved to GEO

IOL	Inter-Orbit Link

Launch id	Launch number that identifies the flight, see LAUNR

LEO	Low Earth Orbit

LHCP	Left Hand Circular Polarization

PAM	Payload Assist Module

Perigee	The orbital point were the satellite is closest from the earth

Polar orbit	Orbit that is perpendicular to the plan of the Equator

Polarization	Plane of vibration of the electrical field of a signal

Power	The transponder amplification power

RADINT	Radar Intelligence

RHCP	Right Hand Circular Polarization

SIGINT	Signal Intelligence

SSPA	Solid State Power Amplifier

THEO	Twelve Hours Excentric Orbit (Molniya-type orbit)

TWTA	Traveling Wave Tube Amplifier

Uplink	The earth to satellite signal path


Printing
 Printing - EIRP maps index

Winhelp is not a very good program for printing. To print a page, use the Print item of the File menu.

To print footprints, you should use the following index: clic on one footprint to display it, then use the File Print function and come back to this page with the Back button of the toolbar.

Beware: we have noted important variations of the printing quality with Winhelp. Grey colors are seldomly properly printed. Check the grey color configuration in the printer panel. If Winhelp doesn't provide good quality printing you should screen shot and print an external tool like Paintbrush.

Footprints

A

Anik E1: C-band

Anik E1: Ku-band

Anik E2: C-band

Anik E2: Ku-band

Apstar 1: C-band

Arabsat 1C: S-band

Arabsat 1C: C-band

Asiasat 1: North beam

Asiasat 1: South beam

Asiasat 2: C-band

Asiasat 2: Ku-band

Astra 1A: Horizontal 1

Astra 1A: Horizontal 2

Astra 1A: Vertical 1

Astra 1A: Vertical 2

Astra 1B: Horizontal 1

Astra 1B: Horizontal 2

Astra 1B: Vertical 1

Astra 1B: Vertical 2

Astra 1C: Horizontal 1

Astra 1C: Horizontal 2

Astra 1C: Vertical 1

Astra 1C: Vertical 2

Astra 1D: Horizontal 1

Astra 1D: Horizontal 2

Astra 1D: Vertical 1

Astra 1D: Vertical 2

Astra 1E: Horizontal 1

Astra 1E: Horizontal 2

Astra 1E: Vertical 1

Astra 1E: Vertical 2

D

DBS 1

DBS 2

DBS 3

DFS Kopernikus 3

E

Eutelsat 1F1: West spot

Eutelsat 1F4: spot beams

Eutelsat 1F4: eurobeam

Eutelsat 1F4: SMS beam

Eutelsat 1F5: spot beams

Eutelsat 1F5: eurobeam

Eutelsat 1F5: SMS beam

Eutelsat 2F1: Super beam

Eutelsat 2F1: Wide beam

Eutelsat 2F2: Super beam

Eutelsat 2F2: Wide beam

Eutelsat 2F3: Super beam

Eutelsat 2F3: Wide beam

Eutelsat 2F4: Super beam

Eutelsat 2F4: Wide beam

Express 1: C-band quasi-global A3 & A5

Express 1: C-band hemispheric A4

Express 1: C-band spot A2

Express 1: Ku-band spot A9

G

Galaxy 1R: C-band Horizontal

Galaxy 1R: C-band Vertical

Galaxy 3R: C-band Horizontal

Galaxy 3R: C-band Vertical

Galaxy 4: C-band Horizontal

Galaxy 4: C-band Vertical

Galaxy 4: Ku-band Horizontal

Galaxy 4: Ku-band Vertical

Galaxy 5: C-band Horizontal

Galaxy 5: C-band Vertical

Galaxy 6: C-band Horizontal

Galaxy 6: C-band Vertical

Galaxy 7: C-band Horizontal

Galaxy 7: C-band Vertical

Galaxy 7: Ku-band Horizontal

Galaxy 7: Ku-band Vertical

Gorizont 18: C-band global A6

Gorizont 18: C-band large hemispheric A4

Gorizont 18: C-band narrow hemispheric A8

Gorizont 18: C-band spot A3

Gorizont 18: Ku-band spot A9

Gorizont 19: C-band global A6

Gorizont 19: C-band large hemispheric A4

Gorizont 19: C-band narrow hemispheric A8

Gorizont 19: Ku-band spot A9

Gorizont 20: C-band global A6

Gorizont 20: C-band large hemispheric A4

Gorizont 20: C-band narrow hemispheric A8

Gorizont 21: C-band global A6

Gorizont 21: C-band large hemispheric A4

Gorizont 21: C-band narrow hemispheric A8

Gorizont 21: Ku-band spot A9

Gorizont 24: C-band global A6

Gorizont 24: C-band large hemispheric A4

Gorizont 24: C-band narrow hemispheric A8

Gorizont 24: C-band spot A3

Gorizont 24: Ku-band spot A9

Gorizont 25: C-band global A6

Gorizont 25: C-band large hemispheric A4

Gorizont 25: C-band narrow hemispheric A8

Gorizont 25: Ku-band spot A9

Gorizont 26: C-band global A6

Gorizont 26: C-band large hemispheric A4

Gorizont 26: C-band narrow hemispheric A8

Gorizont 26: Ku-band spot A9

Gorizont 27: C-band global A6

Gorizont 27: C-band large hemispheric A4

Gorizont 27: C-band narrow hemispheric A8

Gorizont 27: C-band spot A3

Gorizont 27: Ku-band spot A9

Gorizont 28: C-band global A6

Gorizont 28: C-band large hemispheric A4

Gorizont 28: C-band narrow hemispheric A8

Gorizont 28: C-band spot A3

Gorizont 28: Ku-band spot A9

Gorizont 29: C-band global A6

Gorizont 29: C-band large hemispheric A4

Gorizont 29: C-band narrow hemispheric A8

Gorizont 29: Ku-band spot A9

Gorizont 30: C-band global A6

Gorizont 30: C-band large hemispheric A4

Gorizont 30: C-band narrow hemispheric A8

Gorizont 30: Ku-band spot A9

Gorizont 31: C-band global A6

Gorizont 31: C-band large hemispheric A4

Gorizont 31: C-band narrow hemispheric A8

Gorizont 31: Ku-band spot A9

H

Hispasat 1A: Direct TV

Hispasat 1A: Telecommunication to Europe

Hispasat 1A: Telecommunication to America

Hispasat 1B: Direct TV

Hispasat 1B: Telecommunication to Europe

Hispasat 1B: Telecommunication to America

Hotbird 1

I

Insat 2A: C-band

Intelsat 502: C-band

Intelsat 502: Ku-band

Intelsat 506: C-band

Intelsat 506: Ku-band

Intelsat 507: C-band

Intelsat 507: Ku-band

Intelsat 510: C-band

Intelsat 510: Ku-band

Intelsat 511: C-band

Intelsat 511: Ku-band

Intelsat 512: C-band

Intelsat 512: Ku-band

Intelsat 515: C-band

Intelsat 515: Ku-band

Intelsat 601: C-band

Intelsat 601: Ku-band spot East

Intelsat 601: Ku-band spot West

Intelsat 602: C-band

Intelsat 602: Ku-band

Intelsat 603: C-band

Intelsat 603: Ku-band

Intelsat 604: C-band

Intelsat 604: Ku-band

Intelsat 605: C-band

Intelsat 605: Ku-band

Intelsat K: Ku-band to America

Intelsat K: Ku-band to Europe

Intelsat 701: C-band

Intelsat 701: Ku-band

Intelsat 702: C-band

Intelsat 702: Ku-band

Intelsat 703: C-band

Intelsat 703: Ku-band

Intelsat 704: C-band

Intelsat 704: Ku-band

Intelsat 705: C-band

Intelsat 705: Ku-band

Intelsat 706: C-band

Intelsat 706: Ku-band

J

Jcsat 1

Jcsat 2

Jcsat 3: C-band

Jcsat 3: Ku-band

K

Koreasat 1: Ku-band Telecom

Koreasat 1: Ku-band DBS

M

Measat 1: C-band

O

Optus A2: National

Optus A2: Australian spots

Optus A3: National

Optus A3: Australian spots

Optus B1: National

Optus B1: Australian spots

Optus B1: High Performance

Optus B3: National

Optus B3: Australian spots

Optus B3: High Performance

Orion 1: Broad beam to Europe

Orion 1: Spot beams to Europe

Orion 1: Broad beam to US

Orion 1: Spot beams to US

P

Palapa B2P

Palapa B2R

Palapa B4

Palapa C1: C-band: Asean & New Zealand beam

Palapa C1: C-band: Asean beam

Palapa C1: C-band: Asia beam

Palapa C1: Ku-band

Panamsat 1: C-band

Panamsat 1: Ku-band to Europe

Panamsat 1: Ku-band to US

Panamsat 2: C-band, Pacific Rim

Panamsat 2: C-band, Oceania

Panamsat 2: Ku-band

R

Raduga 1-1

Raduga 1-2

Raduga 1-3

Raduga 21

Raduga 22

Raduga 28

Raduga 29

Raduga 30

Raduga 32

S

Satcom C1

Satcom C3

Satcom C4

SBS 6: Horizontal

SBS 6: Vertical

Sirius 1

Solidaridad 2: C-band

Solidaridad 2: Ku-band

Superbird B1: Ku-band

T

TDF 1

TDF 2

TDRS 4: C-band

TELE X

Telecom 2A: C-band

Telecom 2A: Ku-band

Telecom 2B: C-band

Telecom 2B: Ku-band

Telecom 2C: C-band

Telecom 2C: Ku-band

Telstar 301

Telstar 302

Telstar 303

Telstar 401: C-band

Telstar 401: Ku-band

Telstar 402R: C-band

Telstar 402R: Ku-band

Thaicom 1: C-band

Thaicom 1: Ku-band

Thaicom 2: C-band

Thaicom 2: Ku-band

Thor

Turksat 1B: European & Turkish spots


C-band US frequency chart (starting horizontal)
 C-band US frequency chart (starting horizontal) (GHz)

Horizontal Uplink	Horizontal Downlink	Channel	Vertical Downlink	Vertical Uplink
	3.720	1		5.945
5.965		2	3.740
	3.760	3		5.985
6.005		4	3.780
	3.800	5		6.025
6.045		6	3.820
	3.840	7		6.065
6.085		8	3.860
	3.880	9		6.105
6.125		10	3.900
	3.920	11		6.145
6.125		12	3.940
	3.960	13		6.185
6.205		14	3.980
	4.000	15		6.225
6.245		16	4.020
	4.040	17		6.265
6.285		18	4.060
	4.080	19		6.305
6.325		20	4.100
	4.120	21		6.345
6.365		22	4.140
	4.160	23		6.385
6.405		24	4.180


C-band US frequency chart (starting vertical)
 C-band US frequency chart (starting vertical) (GHz)

Horizontal Uplink	Horizontal Downlink	Channel	Vertical Downlink	Vertical Uplink
5.945		1	3.720
	3.740	2		5.965
5.985		3	3.760
	3.780	4		6.005
6.025		5	3.800
	3.820	6		6.045
6.065		7	3.840
	3.860	8		6.085
6.105		9	3.880
	3.900	10		6.125
6.145		11	3.920
	3.940	12		6.125
6.185		13	3.960
	3.980	14		6.205
6.225		15	4.000
	4.020	16		6.245
6.265		17	4.040
	4.060	18		6.285
6.305		19	4.080
	4.100	20		6.325
6.345		21	4.120
	4.140	22		6.365
6.385		23	4.160
	4.180	24		6.405


First in History
 First in History...

1957

04 Oct	First satellite, first Russian satellite, Russia becomes the 1st space power: Sputnik 01

03 Nov	First living creature in space: Sputnik 02

1958

01 Feb	First American satellite, America becomes the 2nd space power: Explorer 01

18 Dec	First telecommunication satellite: Score

1959

13 Oct	First meteorology payload: Explorer 07

1960

03 Nov	First NASA satellite: Explorer 08

1961

12 Apr	First man in space

1962

24 Feb	First phone communication & TV broadcast via satellite: Echo 1

26 Apr	First English satellite: Ariel 1

10 Jul	First active telecommunication satellite and first time a company launchs a satellite: Telstar 1

29 Sep	First Canadian satellite: Alouette 1

1963

16 Jun	First woman in space

1964

19 Aug	First geostationary satellite, first geostationary telecommunication satellite: Syncom 3

15 Dec	First Italian satellite: San Marco 1

1965

26 Nov	First French satellite, France becomes the 3rd space power: Astérix

1967

05 Nov	First geostationary meteorology payload: ATS 3

29 Nov	First Australian satellite: Wresat

1968

17 May	First European satellite: ESRO 2B

1969

21 Jul	First man on the moon

08 Nov	First German satellite: Azur

1970

11 Feb	First Japanese satellite, Japan becomes the 4th space power: Ohsumi

10 Mar	First launch from Kourou: Mika

24 Apr	First Chinese satellite, China becomes the 5th space power: Dong Fang Hong 01

1971

28 Oct	First English launched satellite, UK becomes the 6th space power: Prospero

1974

30 May	First direct broadcasting satellite: ATS 6

30 Aug	First Dutch satellite: ANS

15 Nov	First Spanish satellite: Intasat

19 Dec	First civilian satellite 3-axis stabilized: Symphonie 1

1975

19 May	First Indian satellite: Aryabhata

1976

08 Jul	First Indonesian satellite: Palapa A1

1978

24 Oct	First Czechoslovakian satellite: Magion 1

1980

18 Jul	First Indian launched satellite, India becomes the 7th space power: Rohini 1B

1981

12 Apr	First manned launch of the Shuttle: STS 01

07 Aug	First Bulgarian satellite: Intercosmos Bulgaria 1300

1984

06 Apr	First satellite repared in orbit by the shuttle: SMM

16 Nov	First time satellites were brought back from space: STS 19

1985

08 Feb	First Brazilian satellite: Brazilsat A1

17 Jun	First Mexican satellite: Morelos 1

1986

22 Feb	First Swedish satellite: Viking

1988

19 Sep	First Israeli satellite, Israel becomes the 8th space power: Offek 1

11 Dec	First Luxemburger satellite: Astra 1A

1990

22 Jan	First Argentine satellite: Lusat

16 Jul	First Pakistanese satellite: Badr A

1992

10 Aug	First South Korean satellite: Kitsat A

1993

25 Sep	First Portugese satellite: Posat

18 Dec	First Thai satellite: Thaicom 1

1994

10 Aug	First Turkish satellite: Turksat 1B

1995

31 Aug	First Ukrainian satellite: Sich 1

31 Aug	First Chilean satellite: Fasat Alfa

Sep	PanAmSat becomes the first private company ever to provide global satellite services.

1996

12 Jan	First Malaysian satellite: Measat 1


 ACTS

Advanced Communications Technology Satellite

General

Designation	22796 / 93058B
Launch date	12 Sep 1993
Country of origin	United States
Operator	NASA
Mission	Telecommunications
Geostationary orbit	100°W
Launch vehicle	STS 51

Experimental satellite intended to develop Ka-band mobile services to VSAT terminals from high-data rate personal and transportable terminals.

Contact

NASA

600 Independence Avenue, SW, Washington DC 20546

Tel: +1-202-453-1000

Technical data

Specifications

Prime contractor	GE Astro Space
Platform	GE 4000 modified
Mass at launch	2545 kg
Mass in orbit	1555 kg
Dimensions	2.03 x 2.13 x 1.92 m
Stabilization	3 axis
DC power	BOL: 1770 W (batteries: 2 NiCd of 19 AH each) EOL: 1418 W (no payload operation during eclipse)
Design lifetime	4 years
Telemetry & Command	Ka-band with backup in C-band

Orbit control: Blowdown Hydrazine System with redundant thrusters and 4 tanks

Stationkeeping: +/- 0.05°

Ka-band

Main transponders	4
Backup transponders
Power	40 W (TWTA)
Bandwidth	900 MHz
Coverage	A beam-forming network of 45 horns gives a coverage of about 20% of CONUS providing 3 x 0.3° fixed beams There is a single 1.0° mechanically steered beam
EIRP	spot beam: 60 dBW contiguous sectors: 59 dBW steerable: 53 dBW
Polarization


 AEM 1

Application Explorer Satellite

Also called HCMM (Heat Capacity Mapping Mission)

General

Designation	10818 / 78041A
Launch date	26 Apr 1978
Country of origin	United States
Mission	Scientific: Remote sensing (Earth thermal study)
Perigee/Apogee	560/641 km
Inclination	97.6°
Period	96.7 min
Launch vehicle	Scout #98
End of life

Decay	26 Apr 1978


 AEM 2

Application Explorer Satellite

Also called SAGE (Stratospheric Aerosol and Gas Experiment)

General

Designation	11270 / 79013A
Launch date	18 Feb 1979
Country of origin	United States
Mission	Scientific: high atmosphere study
Perigee/Apogee	456/506 km
Inclination	55°
Period	94.2 min
Launch vehicle	Scout #99
End of life

Decay	11 Apr 1989


 AEM 3

Application Explorer Satellite

Also called Magsat

General

Designation	11604 / 79094A
Launch date	30 Oct 1979
Country of origin	United States
Mission	Scientific: Earth magnetic field study
Perigee/Apogee	352/561 km
Inclination	96.8°
Period	93.7 min
Launch vehicle	Scout #101
End of life

Decay	11 Jun 1980


 Program: Aeros

German scientific program


Program: Aeros

Aeros 1

Aeros 2


 Aeros 1

Also called GRS B

General

Designation	06315 / 72100A
Launch date	16 Dec 1972
Country of origin	Germany
Mission	Scientific: ionosphere study
Perigee/Apogee	223/867 km
Inclination	96.9°
Period	95.6 min
Launch vehicle	Scout #83
Mass at launch	127 kg
End of life

Decay	22 Aug 1973


 Aeros 2

General

Designation	07371 / 74055A
Launch date	16 Jul 1974
Country of origin	Germany
Mission	Scientific: ionosphere study
Perigee/Apogee	224/869 km
Inclination	97.5°
Period	95.6 min
Launch vehicle	Scout #88
Mass at launch	127 kg
End of life

Decay	25 Sep 1975


 Afristar

Also called AfriBSS

General

Designation
Launch date	planned in mid-1998
Country of origin
Mission	Telecommunications
Geostationary orbit	12°W
Launch vehicle	Ariane
Technical data

Specifications

L-band


 Agila 1

General

Designation
Launch date	planned on 31 Dec 1996
Country of origin	Philippine
Operator	Philippine Agila Satellite Inc (PASI)
Mission	Telecommunications
Geostationary orbit	153°E ?
Launch vehicle	Ariane (cost: $78 million)
Launch site

The project is led by the government together with firms like: Philippine Telegraph and Telephone, Smart Communications, Globe Telecom, Eastern telecommunication Philippines, etc.

2 satellites (identical) and 2 ground control stations (in Manila and Cebu, $16.5 million) ordered from Aerospatiale (Agila 1: $97 million, Agila 2: $73 million)

The group (PASI) plans to get an in-orbit satellite

Technical data

Specifications

Prime contractor	Aerospatiale
Platform	Spacebus 3000
Mass at launch
Mass in orbit
Dimension
Solar array
Stabilization
DC power
Design lifetime
C-band

Main transponders	24
Backup transponders
Power
Bandwidth
Coverage	West: India East: US North: China
EIRP
Polarization
Ku-band

Main transponders	12
Backup transponders
Power
Bandwidth
Coverage
EIRP
Polarization

One transponder will be donated to the government


 Program: Agrani

Wireless satellite telecommunications system for India: 2 geostationary satellites operated by Afro-Asian Satellite Communications Ltd. ASC is backed by India's Essel Group

Ordered from Hughes for $700 million; project worth $850 million

enhanced HS-601s with very large antennas, to provide direct links with handheld radios from Clarke orbit. One will cover Africa, the other central Asia from Moscow to Singapore. Gallium-arsenide solar cells and Hughes xenon-ion stationkeeping engines will be used.

One satellite will serve mobile users in 54 countries in Asia, the Middle East and the Indian sub-continent. The other satellite will be focused on Africa. Launch dates are tentatively set for late 1997 and mid 1998. Both satellites will be modified HS-601 spacecraft


 Ajisai

Means "hydrangea", also called EGP

General

Designation	16908 / 86061A
Launch date	12 Aug 1986
Country of origin	Japan
Mission	Scientific: geodesy
Perigee/Apogee	1479/1497 km
Inclination	50°
Period	115.7 min
Launch vehicle	H1
Launch site	Tanegashima

Japanese satellite designed to provide an orbiting benchmark for geodynamical studies of the Earth. Laser retroflectors are mounted on the surface of the spherical satellite to return incident laser radiation to its point of origin.

Technical data

Specifications

Mass at launch	685 kg
Diameter	2.15 m
Stabilization	passive

Payload: Retroflectors mounted on the surface of the sphere

Mission: accurate measurement of the satellite's position with respect to Earth; readjustment of domestic triangulation net for accurate map-making; establishment of ocean geodetic net to position outlying islands.


 Alexis

Also called P89-1

General

Designation	22638 / 93026A
Launch date	23 Apr 1993
Country of origin	United States
Operator	USAF
Mission	Scientific: EUV astronomy
Perigee/Apogee	800 km
Inclination	70°
Period
Launch vehicle	Pegasus #4

When Alexis was launched, a bracket that had been damaged during ground testing broke loose, leaving one of the satellite's four solar panels dangling by only its electrical cabling and throwing off the carefully determined balance of the spin-stabilized spacecraft. When the Alexis team restored contact with the satellite more than two months after launch they discovered that not only did it have a serious wobble, but the spacecraft's magnetometer, which was intended to determine the satellite's orientation by sensing Earth's magnetic field lines, had broken when the solar paddle came loose. The Los Alamos science team and the Aero Astro Inc manufacturers came up with a way to determine the satellite's orientation in May 1994. Since then it has been quite successful.

Alexis was designed to monitored the sky in three narrow energy bands between 0.06 and 0.1 keV; it also carried the Blackbeard experiment to study ionospheric effects on radio transmissions.


 Program: Alouette

Canadian scientific program


Program: Alouette

Alouette 1

Alouette 2


 Alouette 1

General

Designation	00424 / 62049A
Launch date	29 Sep 1962
Country of origin	Canada
Mission	Scientific: ionosphere study
Perigee/Apogee	988/1021 km
Inclination	80.5°
Period	105.2 min
Launch vehicle	Thor Agena B
Launch site	Vandenberg
Mass at launch	145 kg
Technical data

Frequency: 136 MHz


 Alouette 2

General

Designation	01804 / 65098A
Launch date	29 Nov 1965
Country of origin	Canada
Mission	Scientific: ionosphere study
Perigee/Apogee	499/2706 km
Inclination	79.8°
Period	118.3 min
Launch vehicle	Thor Agena B
Launch site	Vandenberg
Mass at launch	147 kg


 Amos 1

Affordable Modular Optimised Satellite

General

Designation
Launch date	planned in May 1996
Country of origin	Israel
Mission	Telecommunications
Geostationary orbit	4°W
Launch vehicle	Ariane

Cost: $250 million. The Israeli government supports the program since 1991 with $15 million per year

Operated by Spacecom (Satellite Communication Services, Ltd.) a joint venture of Gilat Communication Engineering, Israel Aircraft Industries, General Satellite Services Company and MER Services Group

It should be co-located with Amos 2 (CERS?)

Technical data

Specifications

Prime contractor	Israel Aircraft Industries (IAI)
Platform	Amos
Mass at launch	961 kg
Mass in orbit
Length
Width
Height
Solar array	10.55 m span
Stabilization	3 axis
DC power
Design lifetime	10 years
Ku-band (11/14 GHz)

Main transponders	7
Backup transponders
Power	34 W
Bandwidth	72 MHz
Coverage	from Lybia to Iran and Ukraine to Sudan
EIRP	52-54 dBW
Polarization

Would have 3 spots: Middle East, Eastern Europe and Central Europe


Amos 2
 Amos 2? CERS?

Also called Magyarsat or Maggarsat

General

Designation
Launch date	1998
Country of origin	Israel
Mission	Telecommunications
Geostationary orbit	4°W
Launch vehicle
Launch site

4 transponders will be reserved to Hungary

Technical data

Ku-band (10.95 - 11.2 & 11.45 - 11.7 GHz)

Main transponders	16
Backup transponders
Power
Bandwidth	36 MHz
Coverage	at least Central Europe
EIRP	50 dBW
Polarization


 Program: AMPTE

Active Magnetospheric Particle Tracer Explorers

International scientific program; composed of 3 small satellites launched together in geostationary transfer orbit. CCE separated and fired its Star 13 rocket to move to a lower inclination orbit. The IRM satellite then fired its Hercules BE-3 motor to raise its apogee to more than 100 000 km. Finally the British UKS satellite separated from IRM (UKS didn't have propulsion of its own).

Contact

http://sd-www.jhuapl.edu/AMPTE/


Program: AMPTE

AMPTE CCE

AMPTE IRM

AMPTE UKS


 AMPTE CCE

General

Designation	15199 / 84088A
Launch date	16 Aug 1984
Country of origin	United States
Mission	Scientific: magnetophere study
Perigee/Apogee	1121/49671 km
Inclination	4.8°
Period	939.5 min
Launch vehicle	Thor Delta #175

Built by Johns Hopkins APL


 AMPTE IRM

General

Designation	15200 / 84088B
Launch date	16 Aug 1984
Country of origin	Germany
Mission	Scientific: magnetophere study
Perigee/Apogee	560/120000 km
Inclination	27°
Period	2653.4 min
Launch vehicle	Thor Delta #175

Built by the German Max Planck MPE group

End of life

Decay	~ Nov 1987


 AMPTE UKS

General

Designation	15201 / 84088C
Launch date	16 Aug 1984
Country of origin	United Kingdom
Mission	Scientific: magnetophere study
Perigee/Apogee	1002/113417 km
Inclination	26.9°
Period	2659.6 min
Launch vehicle	Thor Delta #175

The IRM satellite created 3 'artifical comets' by releasing lithium and barium into the magnetosphere.


 Program: AMS

Advanced Meteorological Satellite

Military meteorological American program; see DMSP. 3 satellites launched.


 Program: AMSC

Operated by American Mobile Satellite Corporation

For mobile communications, designed to provide mobile voice, fax and data services to land mobile maritime, aeronautical and fixed site customers. The company currently offers fleet management mobile data and position reporting services to the maritime, trucking and rail industries throughout the U.S. via leased satellite capacity.

Contact

American Mobile Satellite Corporation (AMSC)

1150 Connecticut Avenue N.W., Washington, DC 20036, USA

Tel: +1-202-331-5858


Program: AMSC

AMSC 1

AMSC 2


 AMSC 1

Also called MSAT 1

General

Designation	23553 / 95019A
Launch date	7 Apr 1995
Country of origin	United States
Mission	Telecommunications
Geostationary orbit	101°W
Launch vehicle	Atlas Centaur

While testing a transmission was sent to the satellite which caused certain components of the communication payload to overheat. The overheating damaged one of eight output hybrid matrix ports that serve the spotbeams covering the Eastern and Central United States. The other seven hybrid ports are operating in accordance with specifications. The remaining four spotbeams, covering the Mountain and Western portions of the United States, Alaska, Hawaii and the Caribbean, were not affected. Furthermore, adjustments in the operation of the satellite will be made to compensate for the power loss.

The satellite has experienced (in mid-1995) on separate occasions the shutdown of two solid state power amplifiers (SSPA) serving the Mountain, Central, Alaska/Hawaii and Caribbean spotbeams. These spotbeams were designed to be served by eight SSPAs with two spares. As a result of these unusual occurrences, AMSC is currently operating these spotbeams in a seven SSPA configuration which preserves one spare SSPA for such spotbeams.

Technical data

Specifications

Prime contractor	Hughes and SPAR Aerospace
Platform	HS-601
Mass at launch	2550 kg
Mass in orbit	1510 kg
Length	2.27 m
Width	2.27 m
Height	2.27 m
Solar array	20.96 m span
Stabilization	3 axis
DC power	BOL: 3600 W
Design lifetime	12 years
L-band (1545-1559/1646.5-1660.5 MHz)

Main transponders	16
Backup transponders	4
Power	38 W (SSPA)
Bandwidth
Coverage	North America
EIRP	58 dBW
Polarization

Total bandwith: 3200 x 5 KHz

Ku-band

Main transponders	1
Backup transponders	2
Power	100 W (TWTA)
Bandwidth
Coverage	CONUS, Carribean, Alaska and Hawaii
EIRP	36 dBW
Polarization


 AMSC 2

General

Designation
Launch date	planned in mid 1996
Country of origin	United States
Mission	Telecommunications
Geostationary orbit	106.5°W
Launch vehicle	Ariane
Launch site

Same as AMSC 1?


 Program: Anik

In Eskimo language Anik means "brother"

Canadian system owned by Telesat Canada. Canada was the first country to start a domestic telecommunication system because of it's large territory and distributions of its inhabitants. Telesat Canada belongs for half to the State and private companies.

Contact

Telesat Canada

1601 Telesat Court, Gloucester K1B 5P4, Ontario, Canada

Tel: +1-613-748-0123

Fax: +1-613-748-8712

Email: info@telesat.ca

http://www.telesat.ca


Program: Anik

Anik A1	Anik A2	Anik A3
Anik B1
Anik C1	Anik C2	Anik C3
Anik D1	Anik D2
Anik E1	Anik E2


Anik A's specifications

Prime contractor
Platform
Mass at launch	560 kg
Mass in orbit	295 kg
Diameter	1.9 m
Height	3.54 m
Stabilization	spin-stabilized
DC power	250 W minimum (full 46-day eclipse capability)
Design lifetime	7 years


Anik A's C-band

Main transponders	12
Backup transponders
Power
Bandwidth	36 MHz
Coverage
EIRP	33 dBW
Polarization


Anik B's specifications

Prime contractor
Platform
Mass at launch
Mass in orbit
Length
Width
Height
Stabilization
DC power
Design lifetime	7 years


Anik B's C-band

Main transponders	12
Backup transponders
Power
Bandwidth	36 MHz
Coverage
EIRP	36 dBW
Polarization


Anik B's Ku-band

Main transponders	6
Backup transponders
Power
Bandwidth	72 MHz
Coverage
EIRP	47 dBW
Polarization


Anik C's specifications

Prime contractor	Hughes
Platform	HS-376
Mass at launch	1160 kg
Mass in orbit	563 kg
Diameter	2.16 m
Height	6.6 m (2.84 m stowed)
Stabilization	Spin stabilized
DC power	BOL: 1135 W
Design lifetime	10 years


Anik C's Ku-band

Main transponders	16
Backup transponders	4
Power	15 W (TWTA)
Bandwidth	54 MHz
Coverage
EIRP	48 dBW
Polarization	linear


Anik D's specifications

Prime contractor	Spar Aerospace with technology licensed from Hughes
Platform	HS-376
Mass at launch	1240 kg
Mass in orbit	633 kg
Diameter	2.16 m
Height	6.6 m (2.84 m stowed)
Stabilization	Spin stabilized
DC power	BOL: 1000 W
Design lifetime	10 years


Anik D's C-band

Main transponders	24
Backup transponders	6
Power	11.5 W (TWTA)
Bandwidth	36 MHz
Coverage
EIRP	36 dBW
Polarization	linear


Anik E's specifications

Prime contractor	Spar Aerospace with GE Astro
Platform	GE 5000
Mass at launch	2923 kg
Mass in orbit	1781 kg
Length	2.84 m
Width	2.26 m
Height	2.18 m
Solar array	24.3 m span
Stabilization	3 axis
DC power	EOL: 3888 W
Design lifetime	13.5 years


Anik E's C-band

Main transponders	24
Backup transponders	6
Power	11.5 W (SSPA)
Bandwidth	36 MHz
Coverage
EIRP	36 dBW
Polarization	linear


Anik E's Ku-band

Main transponders	16
Backup transponders	2
Power	50 W (TWTA)
Bandwidth	54 MHz
Coverage
EIRP	51 dBW
Polarization	linear


Anik E's C-band EIRP


Anik E's Ku-band EIRP


Anik's Ku-band transponder frequency chart
 Anik's Ku-band transponder frequency chart (GHz)

Horizontal Uplink	Horizontal Downlink	Transponder	Vertical Downlink	Vertical Uplink	Beam
14.017		1	11.717		W, N, E, X
	11.730	17		14.030	E or N
14.043		2	11.743		W, N, E, X
	11.756	18		14.056	E or N
14.078		3	11.778		W, N, E, X
	11.791	19		14.091	E or N
14.104		4	11.804		W, N, E, X
	11.817	20		14.117	E or N
14.139		5	11.839		W, N, E, X
	11.852	21		14.152	E
14.165		6	11.865		W, N, E, X
	11.878	22		14.178	E
14.200		7	11.900		W, N, E, X
	11.913	23		14.213	E
14.226		8	11.926		W, N, E, X
	11.939	24		14.239	E
14.261		9	11.961		W
	11.974	25		14.274	E
14.287		10	11.987		W
	12.000	26		14.300	E
14.322		11	12.022		W
	12.035	27		14.335	E
14.348		12	12.048		W
	12.061	28		14.361	E
14.383		13	12.083		W
	12.096	29		14.396	E
14.409		14	12.109		W
	12.122	30		14.422	E
14.444		15	12.144		W
	12.157	31		14.457	E
14.470		16	12.170		W
	12.183	32		14.483	E

Beams: W: West, E: East, N: North, X: Extended corss-border beam


 Anik A1

Also called Telesat 1

General

Designation	06278 / 72090A
Launch date	10 Nov 1972
Country of origin	Canada
Mission	Telecommunications
Geostationary orbit	114°W
Launch vehicle	Thor Delta #92

Linked 37 earth stations

End of life

Out of service	yes
Technical data

Specifications

Ku-band


 Anik A2

Also called Telesat 2

General

Designation	06437 / 73023A
Launch date	20 Apr 1973
Country of origin	Canada
Mission	Telecommunications
Geostationary orbit	109°W
Launch vehicle	Thor Delta #94
End of life

Out of service	yes
Technical data

Specifications

Ku-band


 Anik A3

Also called Telesat 3

General

Designation	07790 / 75038A
Launch date	7 May 1975
Country of origin	Canada
Mission	Telecommunications
Geostationary orbit	104°W
Launch vehicle	Thor Delta #110
End of life

Out of service	yes
Technical data

Specifications

Ku-band


 Anik B1

Also called Telesat 4

General

Designation	11153 / 78116A
Launch date	16 Dec 1978
Country of origin	Canada
Mission	Telecommunications
Geostationary orbit	109°W
Launch vehicle	Thor Delta #147
Mass in orbit	473 kg
End of life

Out of service	yes
Technical data

Specifications

C-band

Ku-band


 Anik C1

Also called Telesat 9

General

Designation	15642 / 85028B
Launch date	13 Apr 1985
Country of origin	Canada
Mission	Telecommunications
Geostationary orbit	72°W
Launch vehicle	STS 23

Was sold to Paracomsat an Argentine operator

Contact

Paracomsat

25 de Mayo 516, 6 Piso, (1002) Buenos Aires -- Argentina

Tel: +54-1-313-5058 or 313-5158 or 313-9829

Fax: +54-1-311-1852

Technical data

Specifications

Ku-band

Ku-band transponder frequency chart


 Anik C2

Also called Telesat 7

General

Designation	14133 / 83059B
Launch date	18 Jun 1983
Country of origin	Canada
Mission	Telecommunications
Geostationary orbit	see below
Launch vehicle	STS 07

Was sold to Paracomsat an Argentine operator

Contact

Paracomsat

25 de Mayo 516, 6 Piso, (1002) Buenos Aires -- Argentina

Tel: +54-1-313-5058 or 313-5158 or 313-9829

Fax: +54-1-311-1852

Location

Begin	End	Position
L: 18 Jun 1983		76.2°W
Feb 1995		75.8°W, inclined

Inclined since Aug 1993; should reach EOL in 1996

Technical data

Specifications

Ku-band

Ku-band transponder frequency chart


 Anik C3

Also called Telesat 5

General

Designation	13652 / 82110C
Launch date	12 Nov 1982
Country of origin	Canada
Mission	Telecommunications
Geostationary orbit	114.9°W, inclined
Launch vehicle	STS 05
Technical data

Specifications

Ku-band

Ku-band transponder frequency chart


 Anik D1

Also called Telesat 6

General

Designation	13431 / 82082A
Launch date	26 Aug 1982
Country of origin	Canada
Mission	Telecommunications
Geostationary orbit	104.5°W
Launch vehicle	Thor Delta #164
End of life

Out of service	Feb 1995
Technical data

Specifications

C-band


 Anik D2

Also called Telesat 8 or Satcom 4R

General

Designation	15383 / 84113B
Launch date	9 Nov 1984
Country of origin	Canada
Mission	Telecommunications
Geostationary orbit	see below
Launch vehicle	STS 19

Replaced Anik 1B in November 1986.

Was sold in September 1993 and became Arabsat 1D

Location

Begin	End	Position
L: 9 Nov 1984		?
May 1992	May 1992	82°W (Satcom 4R)
?		110.5°W (Anik D2)
September 1993		20°E (Arabsat 1D)
End of life

Out of service	Mar 1995
Cause	Sent to the junk orbit
Technical data

Specifications

C-band


 Anik E1

Also called Telesat 11

General

Designation	21726 / 91067A
Launch date	26 Sep 1991
Country of origin	Canada
Mission	Telecommunications
Geostationary orbit	111°W
Launch vehicle	Ariane V46

On January 20th, 1994 at 12:50 local time, the satellite ran out of control and thus all transmissions were interrupted. Control was regained at 19:00 and at 20:15 all was back into order. Soon after, it was Anik E2's turn! Those technical hitch were caused by magnetic storms.

At 10:47 UT on March 26, 1996 Telesat lost both the C and Ku-bands on the satellite. This was caused by the disconnection of the South solar pannel... gone away!

Technical data

Specifications

C-band

Ku-band

C-band transponder frequency chart

Ku-band transponder frequency chart

EIRP coverage (dBW)

C-band

Ku-band


 Anik E2

Also called Telesat 10

General

Designation	21222 / 91026A
Launch date	5 Apr 1991
Country of origin	Canada
Mission	Telecommunications
Geostationary orbit	107.3°W
Launch vehicle	Ariane V43

After Anik E1's incident, this satellite run out of control January 20th, 1994 at 21:00 local time after a magnetic storm. It distroyed the on-board stabilization system. To face this problem, Telesat has built a system that calculates and orders the satellite's movements from an Earth station.

This satellite was already victim of technical problems after launch to position its antennas.

Technical data

Specifications

C-band

Ku-band

C-band transponder frequency chart

Ku-band transponder frequency chart

EIRP coverage (dBW)

C-band

Ku-band


 Anna 1B

General

Designation	00446 / 62060A
Launch date	31 Oct 1962
Country of origin	United States
Mission	Scientific: Geodesy
Perigee/Apogee	1075/1181 km
Inclination	50.1°
Period	107.9 min
Launch vehicle	Thor Ablestar
Launch site	Cape Canaveral


 ANS

Astronomical Netherlands Satellite

General

Designation	07427 / 74070A
Launch date	30 Aug 1974
Country of origin	Netherlands
Mission	Scientific: UV and X-ray astronomy
Perigee/Apogee	268/2174 km
Inclination	98°
Period	99.1 min
Launch vehicle	Scout #89
Mass at launch	130 kg

First Dutch satellite

End of life

Decay	14 Jun 1977


 Apex

Advanced Photovoltaic and Electronic eXperiments, also called P90-6

General

Designation	23191 / 94046A
Launch date	3 Aug 1994
Country of origin	United States
Mission	Scientific: magnetosphere study
Perigee/Apogee	360/2534 km
Inclination	69.9°
Period	115 min
Launch vehicle	Pegasus #7
Mass at launch	260 kg

Carries a variety of advanced solar cell experiments for the US Air Force: Photovoltaic Array and Space Power Plus Diagnostics (PASP-Plus), Ferroelectric Experiment (FERRO), and Cosmic Ray Upset Experiment (CRUX) to check the impact of radiation in the Van Allen belt on the other two target instruments.

Technical data

Platform: Pegastar


APMT
 Program: APMT

Asia Pacific Mobile Telecommunications

Hughes signed a $640 million contract awarded by a consortium of Chinese and Singaporean companies to provide satellite and ground communications equipment. The system will allow callers across a wide range of Asia to use mobile phones in areas without cellular or fixed-line service.

Should be operational in 1998, 2 satellites to be launched by Long March

APMT groups four Chinese companies, as well as Singapore Telecom and Singapore Technologies Telemedia. The Chinese participants are China Aerospace Corp, China Unicom Satellite Telecommunication Co Ltd, China Telecommunications Broadcast Satellite Corp, and China Satellite Launch and Tracking Control General.


 Apple

Ariane Passenger PayLoad Experiment

General

Designation	12545 / 81057B
Launch date	19 Jun 1981
Country of origin	India
Operator	ISRO
Mission	Telecommunications, experimental
Geostationary orbit	102°E
Launch vehicle	Ariane L03
Mass at launch	670 kg
End of life

Out of service	19 Sep 1983


 Program: Apstar

Hong Kong program operated by Asia Pacific Telecommunication (APT) owned by Chinese, Hong Kong and other Asian countries

Contact

Asia Pacific Telecommunication Satellites Company

Room 3111-2, 31st floor, One Pacific Plaza, 88 Queens way, Hong Kong

Tel: +852-526-2281

Fax: +852-522-0419


Program: Apstar

Apstar 1

Apstar 1A

Apstar 2

Apstar 2R


 Apstar 1

General

Designation	23185 / 94043A
Launch date	21 Jul 1994 at 10:55 UT
Country of origin	Hong Kong
Mission	Telecommunications
Geostationary orbit	138°E
Launch vehicle	Long March 3
Launch site	Xichang

The satellite was to be slotted at 131°E but this was too close from Sakura 3A (132°E) and Gorizont 29 (130°E). After protests from in-orbit satellite operators a slot at 138°E was leased to Tonga (for about $15 million).

Technical data

EIRP coverage (dBW)

Specifications

Prime contractor	Hughes
Platform	HS-376
Mass at launch	1400 kg
Mass in orbit	650 kg
Diameter	2.16 m
Height	6.8 m deployed
Stabilization	Spin stabilized
DC power	EOL: 1022 W
Design lifetime	10 years
Beacons	Telemetry: 4.199375 & 4.199575 GHz Command: 5.928 GHz
C-band

Main transponders	24
Backup transponders
Power	16 W
Bandwidth	20 transponders of 36 MHz 4 transponders of 72 MHz
Coverage & EIRP	South East Asia, up to 36 dBW
Polarization	linear


Apstar 1's C-band EIRP


 Apstar 2

General

Launch date	25 Jan 1995 at 19:26 UT
Country of origin	Hong Kong
Mission	Telecommunications
Geostationary orbit	should have been in 77°E slot
Launch vehicle	Long March 2E
Launch site	Xichang

Six people had been killed by falling debris from the explosion which also injured 27.

End of life

Out of service	25 Jan 1995
Cause	Exploded of the satellite shortly after launcher. Failure Review attributed the failure to wind shear interaction with the vehicles structure and the inability of the rather rudimentary control and guidance system of the Long March 2E to account for this.
Technical data

Specifications

Prime contractor	Hughes
Platform	HS-601
Stabilization	3 axis
C-band

Main transponders	26
Backup transponders
Power	52 W
Bandwidth
Coverage
EIRP
Polarization
Ku-band

Main transponders	8
Backup transponders
Power	6 transponders at 50 W 2 transponders at 120 W
Bandwidth
Coverage
EIRP
Polarization


 Apstar 2R

General

Designation
Launch date	planned in Dec 1996
Country of origin	Hong Kong
Mission	Telecommunications
Geostationary orbit	77°E
Launch vehicle	Long March 3B
Launch site	Xichang
Technical data

Specifications

Prime contractor	Space Systems/Loral
Platform	FS-1300
Mass at launch
Mass in orbit
Dimension
Solar array
Stabilization
DC power
Design lifetime
C-band

Main transponders	28
Backup transponders
Power	60 W
Bandwidth
Coverage
EIRP
Polarization
Ku-band

Main transponders	16
Backup transponders
Power	110 W
Bandwidth
Coverage
EIRP
Polarization


 Apstar 1A

General

Designation
Launch date	planned in early 1996
Country of origin	Hong Kong
Mission	Telecommunications
Geostationary orbit	planned in 121°E (dispute with Thaicom 3)
Launch vehicle	Long March 3
Launch site

This satellite should be based on a HS-376 to cover the same area as Apstar 1 + the Indian sub-continent. 24 transponders Will backup Apstar 1

Mass will not be over 1500 kg


 Program: Arabsat

Satellite program of the Arab States operated by Arabsat also known as Arabsat Satellite Communications Organization (ASCO)

In 1976 22 countries decided to build, launch and operate their own telecommunications geostationary satellites. At this time the Arabsat project was an innovation because even if Canada (Anik) and the United States (Comstar, Satcom and Westar) had their own satellites it was only for national communications. 3 satellites were ordered in 1981 to Aérospatiale and the Earth stations were build from 1983 on by Japanese companies.

Contact

Arabsat

PO Box 1038, 11431 Riyadh, Saudi Arabia

Tel: +966-1-464-6666

Fax: +966-1-465-6983


Program: Arabsat

Arabsat 1A	Arabsat 1B	Arabsat 1C	Arabsat 1D	Arabsat 1E
Arabsat 2A	Arabsat 2B


Arabsat 1A, 1B & 1C's specifications

Prime contractor	Aerospatiale
Platform	Spacebus 100
Mass in orbit	700 kg
Payload mass	122.4 kg: 101.4 kg: transponders, 21 kg: antennas
Dimension	2.26 x 1.64 x 2.26 m
Solar array	20.7 m span
Stabilization	3 axis
DC power	EOL: 1400 W (equinox), 1300 W (solstice)
Payload power	990.5 W
Design lifetime	7 years


Arabsat 1A, 1B & 1C's S-band

Main transponders	1
Backup transponders
Power	2 x 50 W (TWTA)
Bandwidth	33 MHz
Coverage
EIRP	41 dBW
Polarization	linear V


Arabsat 1A, 1B & 1C's C-band

Main transponders	25
Backup transponders
Power	8.5 W
Bandwidth	33 MHz
Coverage
EIRP	31 dBW
Polarization	circular


Arabsat 2's specifications

Prime contractor	Aerospatiale
Platform	Spacebus 3000
Mass at launch	2415 kg
Payload mass	260 kg
Dimension	2.4 x 1.6 x 2.3 m
Stabilization	3 axis
DC power	EOL: 5000 W
Design lifetime	12 years


Arabsat 2's C-band

Main transponders	14 + 8
Backup transponders	6 + 4
Power	14 transponders of 15 W (SSPA) 8 transponders of 55 W (SSPA)
Bandwidth	33 MHz
Coverage	Arab States
EIRP	15 W transponders: 35 dBW 52 W transponders: 41 dBW
Polarization	circular
Frequencies	Uplink: 5.925-6.425 GHz Downlink: 3.7-4.2 GHz


Arabsat 2's Ku-band

Main transponders	12
Backup transponders	5
Power	90 W (TWTA)
Bandwidth	33 MHz
Coverage	Arab States
EIRP	47 dBW
Polarization	linear
Frequencies	Uplink: 13.750-14.000 GHz Downlink: 12.5-12.75 GHz


 Arabsat 1A

General

Designation	15560 / 85015A
Launch date	8 Feb 1985
Country of origin	Arab States
Mission	Telecommunications
Geostationary orbit	19°E
Launch vehicle	Ariane V12
Mass at launch	1170 kg

In Sep 1991 the satellite started drifting East and was completly lost in Mar 1992.

End of life

Out of service	Mar 1992
Cause	Out of control
Technical data

Specifications

S-band

C-band


 Arabsat 1B

General

Designation	15825 / 85048C
Launch date	18 Jun 1985
Country of origin	Arab States
Mission	Telecommunications
Geostationary orbit	26°E
Launch vehicle	STS 25
Mass at launch	1270 kg

In Oct 1992 the satellite started drifting East and was completly lost in early 1993.

End of life

Out of service	early 1993
Cause	Out of control
Technical data

Specifications

S-band

C-band


 Arabsat 1C

General

Designation	21894 / 92010B
Launch date	26 Feb 1992
Country of origin	Arab States
Mission	Telecommunications
Geostationary orbit	31°E
Launch vehicle	Ariane V49
Mass at launch	1360 kg
Technical data

Specifications

S-band

C-band

S-band EIRP coverage (dBW)

C-band EIRP coverage (dBW)

Beacons: 3.7031 & 4.1999 GHz


Arabsat 1C's S-band EIRP


Arabsat 1C's C-band EIRP


 Arabsat 1D

General

Old name	Anik D2
Country	Arab States
Mission	Telecommunications

Bought in September 1993. A year after it started to have stabilisation problems and to consume alot of propellant.

Location

Begin	End	Position
L: 8 Nov 1984	1993	110.5°W
Sep 1993	Dec 1994...	20°E
Feb 1995	Feb 1995	19°E
End of life

Out of service	Mar 1995
Cause	Sent to the junk orbit


 Arabsat 1E

Also called Arabsat 1DR

General

Old name	Telstar 301
Country	Arab States
Mission	Telecommunications

Leased in January 1995 to replace Arabsat 1D

Location

Begin	End	Position
L: 26 Aug 1982	1994	104.5°W
Jan 1995		20°E, inclined


 Arabsat 2A

General

Designation
Launch date	planned in 1996
Country of origin	Arab States
Mission	Telecommunications
Geostationary orbit	19°E
Launch vehicle	Ariane
Launch site
Mass at launch	2415 kg

Allocations:

Ku-band - Saudi Arabia (3), Qatar, Kuwait, Syria and Jordan (1) - 4 free

C-band - 41dBW - Saudi Arabia (3), Oman (1) - free 4

C-band - 35 dBW - Egypt, Bahrain, Mauritius, Sudan, UAE (1) - 8 free

Technical data

Specifications

C-band

Ku-band


 Arabsat 2B

General

Designation
Launch date	planned in 1996?
Country of origin	Arab States
Mission	Telecommunications
Geostationary orbit	26°E
Launch vehicle	Ariane
Launch site
Technical data

Specifications

C-band

Ku-band


 Program: Argos

Localization and data transmission program. Was created by French and American organizations (CNES/NASA/NOAA). Started in 1978, it uses fixed or mobile instruments for meteorology with an transmitter.

The ARGOS/DCS, provided by France, assists NOAA in its overall environmental mission and in the support of the Global Atmospheric Research Program. Approximately 2,000 platforms (buoys, free- floating balloons and remote weather stations) measure temperatures, pressure and altitude, and they transmit these data to the satellite. The onboard DCS receives the incoming signal, measures both the frequency and the relative time of occurrence of each transmission, and retransmits these data to the central processing facility. The DCS information is then sent to the CNES ARGOS processing center, where it is processed, distributed and stored on magnetic tape for archival purposes. The data rate is 720 bps.

The system is actually only 20% booked with 2500 beacons and 170 users. The reception stations are:Fairbanks, Alaska; Wallops Island, Virginia US; Lannion, France.

Contact

North America:

Service Argos Inc.

Suite 10, Mc Cormick Drive, Landover MD 20785 -- USA

Tel: +1-301-925-4411

Fax: +1-301-925-8995

Telex: 898 146

Other parts of the World:

CLS Argos

18, avenue Edouard Belin, 31055 Toulouse Cedex -- FRANCE

Tel: +33-6139-4700

Fax: +33-6175-1014

Telex: 531 752 F


 Program: Ariel

First English space program


Program: Ariel

Ariel 1

Ariel 2

Ariel 3

Ariel 4

Ariel 5

Ariel 6


 Ariel 1

General

Designation	00285 / 62015A
Launch date	26 Apr 1962
Country of origin	United Kingdom
Mission	Scientific: ionosphere study
Perigee/Apogee	398/1203 km
Inclination	53.8°
Period	100.8 min
Launch vehicle	Thor Delta #9
End of life

Decay	24 May 1976


 Ariel 2

General

Designation	00771 / 64015A
Launch date	27 Mar 1964
Country of origin	United Kingdom
Mission	Scientific: ionosphere and high atmosphere study
Perigee/Apogee	287/1349 km
Inclination	51.7°
Period	101.3 min
Launch vehicle	Scout #25
End of life

Decay	18 Nov 1967


 Ariel 3

General

Designation	02773 / 67042A
Launch date	5 May 1967
Country of origin	United Kingdom
Mission	Scientific: ionosphere and high atmosphere study
Perigee/Apogee	499/604 km
Inclination	80.6°
Period	95.6 min
Launch vehicle	Scout #53

First satellite entirely build in the UK

End of life

Decay	14 Dec 1970


 Ariel 4

General

Designation	05675 / 71109A
Launch date	11 Dec 1971
Country of origin	United Kingdom
Mission	Scientific: ionosphere and high atmosphere study
Perigee/Apogee	476/592 km
Inclination	82°
Period	95.3 min
Launch vehicle	Scout #78
End of life

Decay	12 Dec 1978


 Ariel 5

General

Designation	07471 / 74077A
Launch date	15 Oct 1974
Country of origin	United Kingdom
Mission	Scientific: X-ray astronomy
Perigee/Apogee	504/549 km
Inclination	2.9°
Period	94.9 min
Launch vehicle	Scout #90
End of life

Decay	14 Mar 1980


 Ariel 6

General

Designation	11382 / 79047A
Launch date	2 Jun 1979
Country of origin	United Kingdom
Mission	Scientific: X-ray astronomy
Perigee/Apogee	472/383 km
Inclination	55°
Period	92.1 min
Launch vehicle	Scout #100
End of life

Decay	23 Sep 1990


 Arsène

Ariane Radio-astronome Satellite ENseignement Espace

General

Designation	22654 / 93031B
Launch date	12 May 1993
Country of origin	France
Mission	Telecommunications
Perigee/Apogee	17261/36793 km
Inclination	1.8°
Period	1012.7 min
Launch vehicle	Ariane V56
Mass at launch	154 kg

Built by Sup Aéro students with the help of RACE (Radio Amateur Club de l'Espace). Made from recovery material.

End of life

Out of service	October 1993
Cause	Failure
Technical data

Packet radio uplink	1200baud, BELL 202 (standard VHF packet radio) AFSK (FM) 435.0625 435.1125 435.1375 MHz
Packet radio downlink	1200baud, BELL 202 AFSK (FM) 145.975 MHz

S-Mode linear transponder:

CW telemetry beacon	2446.4700 MHz, 110lpm CW
S-mode uplink	435.0625 MHz +/- 8kHz
S-mode downlink	2446.5025 MHz +/- 8kHz

Has a SEP Mars apogee motor


 Aryabhata

General

Designation	07752 / 75033A
Launch date	19 May 1975
Country of origin	India
Mission	Scientific: ionosphere study
Perigee/Apogee	398/409 km
Inclination	50.7°
Period	92.6 min
Launch vehicle	Intercosmos
Launch site	Kapustin Yar
Mass at launch	360 kg

Studies astronomy sources and relations between Earth and Sun.

End of life

Out of service	After 4 days
Cause	Failure
Decay	11 Feb 1992


 Program: ASC

American Satellite Company

Program from ASC and CONTEL (CONtinental TELephone company). The satellites are used for GATS (Global Access Telecommunications Services).


Program: ASC

ASC 1

ASC 2


ASC's specifications

Prime contractor	GE Astro Space
Platform	GE 3000
Mass at launch	1250 kg
Mass in orbit	665 kg
Dimension	1.63 x 1.32 x 0.99 m
Solar array	14.33 m span
Stabilization	3 axis
Design lifetime	10 years


ASC's C-band transponder frequency chart
 ASC's C-band transponder frequency chart (GHz)

Horizontal Uplink	Horizontal Downlink	Transponder	Channel	Vertical Downlink	Vertical Uplink
	3.720	1	1		5.945
5.965		13L	2	3.740
	3.760	2	3		5.985
6.005		13U	4	3.780
	3.800	3	5		6.025
6.045		14L	6	3.820
	3.840	4	7		6.065
6.085		14U	8	3.860
	3.880	5	9		6.105
6.125		15L	10	3.900
	3.920	6	11		6.145
6.125		15U	12	3.940
	3.960	7	13		6.185
6.205		16L	14	3.980
	4.000	8	15		6.225
6.245		16U	16	4.020
	4.040	9	17		6.265
6.285		17L	18	4.060
	4.080	10	19		6.305
6.325		17U	20	4.100
	4.120	11	21		6.345
6.365		18L	22	4.140
	4.160	12	23		6.385
6.405		18U	24	4.180


ASC's Ku-band transponder frequency chart (GHz)

Horizontal Downlink	Transponder	Vertical Uplink
11.740	19	14.040
11.820	20	14.120
11.900	21	14.200
11.980	22	14.280
12.060	23	14.360
12.140	24	14.440


 ASC 1

General

Designation	15994 / 85076C
Launch date	27 Aug 1985
Country of origin	United States
Mission	Telecommunications
Geostationary orbit	128°W
Launch vehicle	STS 27
End of life

Out of service	Nov 1994?
Technical data

Specifications

C-band transponder frequency chart

Ku-band transponder frequency chart

C-band

Main transponders	18
Backup transponders
Power	36 MHz: 12 of 8.5 W (SSPA) 72 MHz: 6 of 16.2 W (TWTA)
Bandwidth	12 of 36 MHz 6 of 72 MHz
Coverage
EIRP	34 dBW
Polarization	linear
Ku-band

Main transponders	6
Backup transponders
Power	16.2 W (TWTA)
Bandwidth	72 MHz
Coverage
EIRP	42 dBW
Polarization	linear H


 ASC 2

Otherwise knowned as Spacenet 4

General

Designation	21227 / 91028A
Launch date	13 Apr 1991
Country of origin	United States
Mission	Telecommunications
Geostationary orbit	101°W
Launch vehicle	Delta 2 #204
Technical data

Specifications

C-band transponder frequency chart

Ku-band transponder frequency chart

C-band

Main transponders	18
Backup transponders
Power	36 MHz: 12 of 8.5 W (SSPA) 72 MHz: 6 of 16 W (TWTA)
Bandwidth	12 of 36 MHz 6 of 72 MHz
Coverage
EIRP	37 dBW
Polarization	linear
Ku-band

Main transponders	6
Backup transponders
Power	6 of 16.2 W (TWTA) 2 of 30 W (TWTA)
Bandwidth	72 MHz
Coverage
EIRP	46 dBW
Polarization	linear H


 Program: Asiasat

Telecommunication program. Asiasat is equally owned by Hong Kong's Hutchison Whampoa Ltd, Beijing's China International Trust and Investment Corp (CITIC) and Britain's Cable and Wireless Plc

Contact

Asia Satellite Telecommunications Company Ltd

23-24/F, East Exchange Tower, 38-40 Leighton Road, Causeway Bay, Hong Kong

Tel: +852-805-6666

Fax: +852-576-4111


Program: Asiasat

Asiasat 1

Asiasat 2

Asiasat 3


 Asiasat 1

General

Designation	20558 / 90030A
Launch date	7 Apr 1990
Country of origin	Hong Kong
Mission	Telecommunications
Geostationary orbit	105.5°E
Launch vehicle	Long March 3
Launch site	Xichang

This satellite was Westar 6 that was brought back from Space by the Shuttle in 1984. It was bought for only $58 million

Technical data

Specifications

Prime contractor	Hughes
Platform	HS-376
Mass at launch	1244 kg
Mass in orbit	620 kg
Diameter	2.16 m
Height	6.6 m (2.84 m stowed)
Stabilization	Spin stabilized
DC power	BOL: 850 W
Design lifetime	9 years
C-band

Main transponders	24
Backup transponders	6
Power	8.5 W (TWTA)
Bandwidth	36 MHz
Coverage and EIRP	North beam: 36 dBW South beam: 37 dBW
Polarization	linear
Transponder frequency chart (GHz)

Horizontal Downlink	Transponder	Vertical Downlink
	1	3.740
3.760	2
	3	3.780
3.800	4
	5	3.820
3.840	6
	7	3.860
3.880	8
	9	3.900
3.920	10
	11	3.940
3.960	12
	13	3.980
4.000	14
	15	4.020
4.040	16
	17	4.060
4.080	18
	19	4.100
4.120	20
	21	4.140
4.160	22
	23	4.180
4.200	24


Asiasat 1's EIRP (North beam)


Asiasat 1's EIRP (South beam)


 Asiasat 2

General

Designation	23723 / 95064A
Launch date	28 Nov 1995 at 11:30 UT
Country of origin	Hong-Kong
Mission	Telecommunications
Geostationary orbit	100.5°E
Launch vehicle	Long March 2E (38th LM launch)
Launch site	Xichang

Second stage orbit: 185 km x 309 km x 28° Then the Chinese perigee kick motor SPTM-17 (second flight) lifted Asiasat to 222 x 35039 km x 25.6° and the liquid apogee motor (a Leros-class dual mode liquid apogee engine built by Royal Ordnance plc, England) then circularized the orbit.

Cost: $200 million

Technical data

EIRP coverage (dBW)

C-band

Ku-band

Specifications

Prime contractor	GE Astro Space
Platform	GE 7000
Mass at launch	3460 kg
Mass in orbit	1500 kg
Length
Width
Height
Stabilization	3 axis
DC power	BOL: 7100 W
Design lifetime	15 years

The perigee engine was made in China and is being used for the first time.

C-band

Main transponders	24
Backup transponders	6
Power	55 W (TWTA)
Bandwidth	20 transponders at 36 MHz 4 transponders at 72 MHz
Coverage	Asia and Australia
EIRP	39 dBW
Polarization	Linear
Frequencies	Uplink: 5.845-6.425 GHz Downlink: 3.625-4.2 GHz
Ku-band

Main transponders	9
Backup transponders
Power	115 W (TWTA)
Bandwidth	54 MHz
Coverage	China and nearby countries
EIRP	52 dBW
Polarization	Linear
Frequencies	Uplink: 14.0-14.3 GHz Downlink: 12.2-12.5 GHz


Asiasat 2's C-band EIRP


Asiasat 2's Ku-band EIRP


 Asiasat 3

General

Designation
Launch date	planned in late 1997
Country of origin	Hong-Kong
Mission	Telecommunications
Geostationary orbit	122°E
Launch vehicle	Proton
Launch site

The Long March vehicle was abandonned after the Intelsat 708 crash.

Technical data

Specifications

Prime contractor	Hughes
Platform	HS-601HP
Mass at launch
Mass in orbit
Dimension
Solar array
Stabilization
DC power	~7000 W
Design lifetime	15 years
C-band

Main transponders	28
Backup transponders
Power
Bandwidth
Coverage	Asia, the Indian subcontinent, the Middle East and Australia
EIRP
Polarization
Ku-band

Main transponders	16
Backup transponders
Power
Bandwidth
Coverage	2 beams: 1 for China & 1 for India + 1 steerable beam
EIRP
Polarization


 Asiastar

Also called AsiaBSS

General

Designation
Launch date	planned in late-1998
Country of origin	United States
Mission	Telecommunications
Geostationary orbit	105°E
Launch vehicle	Ariane
Technical data

Specifications

L-band


 Astérix

Also called A1

General

Designation	01778 / 65096A
Launch date	26 Nov 1965 at 15:47 local time
Country of origin	France
Mission	Scientific
Perigee/Apogee	527/1697 km
Inclination	64.3°
Period	107.5 min
Launch vehicle	Diamant #1
Mass at launch	42 kg

First launch of a French satellite by a French launcher; makes France the 3rd space power.

It's antenna was damaged during launch thus the technological capsule didn't provide any data

End of life

Out of service	26 Nov 1965
Cause	Never transmited


 Program: Astra

Direct Broadcasting System that covers western Europe. Operated by SES (Société Européenne de Satellites), a compagny founded in March 1985 by 11 shareholders. Its center is located at the Betzdorff castle in Luxemburg.

Contact

SES

Château de Betzdorf, 6815 Betzdorf, Luxembourg

Tel: +352-710-7251

Fax: +352-710-725324

Technical data

Modulation

Bandwidth	26 MHz
Video excursion	16 MHz/v
Mono bandwidth	180 KHz
Mono de-emphasis	50 µs
Stereo bandwidth	130 KHz
Stereo de-emphasis	75 µs
Stereo expansion	Panda 1


Program: Astra

Astra 1A

Astra 1B

Astra 1C

Astra 1D

Astra 1E

Astra 1F

Astra 1G

Astra 1H

Astra 2A


 Astra 1A

General

Designation	19688 / 88109B
Launch date	11 Dec 1988
Country of origin	Luxemburg
Mission	Direct TV
Geostationary orbit	19.2°E
Launch vehicle	Ariane V27

TV programs started on 5 Feb 1989. In 1994 a few transponders were taken over by Astra 1C because of technical problems.

Astra 1A will probably be used for satellite news gathering duties from 1998 onwards (after Astra 1H is in position), being placed in an inclined orbit, and moved to either 24.3, 26, or 28.2 degrees East. ("What Satellite TV")

Technical data

EIRP coverage (dBW)

Horizontal polarization mode 1

Horizontal polarization mode 2

Vertical polarization mode 1

Vertical polarization mode 2

Specifications

Prime contractor	GE Astro Space
Platform	GE 4000
Mass at launch	1800 kg
Payload mass	230 kg: transponders: 184 kg, antennas: 46 kg
Dimension	2.9 x 1.6 x 1 m
Solar array	19.3 m span
Stabilization	3 axis
DC power	BOL: equinox: 2236 W, solstice: 2057 W
Payload power	1674.4 W
Design lifetime	10 years
Beacon	11.20300 GHz vertical 11.44650 GHz horizontal
Ku-band (11.2-11.45 GHz)

Main transponders	16
Backup transponders	6
Power	45 W
Bandwidth	26 MHz
Coverage	Europe
EIRP	50 dBW
Polarization	linear
Uplink	14.25-14.5 GHz
Transponder frequency chart (GHz)

Horizontal Downlink	Beam	Channel	Vertical Downlink
11.21425	H1	1
	V2	2	11.22900
11.24375	H2	3
	V1	4	11.25850
11.27325	H1	5
	V2	6	11.28800
11.30275	H2	7
	V1	8	11.31750
11.33225	H1	9
	V2	10	11.34700
11.36175	H2	11
	V1	12	11.37650
11.39125	H1	13
	V2	14	11.40600
11.42075	H2	15
	V1	16	11.43550


Astra 1A's EIRP (H polarization mode 1)


Astra 1A's EIRP (H polarization mode 2)


Astra 1A's EIRP (V polarization mode 1)


Astra 1A's EIRP (V polarization mode 2)


 Astra 1B

General

Designation	21139 / 91015A
Launch date	2 Mar 1991
Country of origin	Luxemburg
Mission	Direct TV
Geostationary orbit	19.2°E
Launch vehicle	Ariane V42
Technical data

EIRP coverage (dBW)

Horizontal polarization mode 1

Horizontal polarization mode 2

Vertical polarization mode 1

Vertical polarization mode 2

Specifications

Prime contractor	GE Astro Space
Platform	GE 5000
Mass at launch	2580 kg
Mass in orbit	1562 kg
Payload mass	354 kg: transponders: 308 kg, antennas: 46 kg
Dimension	2.2 x 2.9 x 2.3 m
Solar array	21.5 m span
Stabilization	3 axis
DC power	BOL: equinox: 2790 W, solstice: 2567 W
Payload power	2136 W
Design lifetime	10 years
Beacon	11.45350 GHz vertical 11.69650 GHz horizontal
Ku-band (11.45-11.7 GHz)

Main transponders	16
Backup transponders	6
Power	60 W
Bandwidth	26 MHz
Coverage	Europe
EIRP	52.5 dBW
Polarization	linear
Uplink	14.0-14.25 GHz
Transponder frequency chart (GHz)

Horizontal Downlink	Beam	Channel	Vertical Downlink
11.46425	H1	17
	V2	18	11.47900
11.49375	H2	19
	V1	20	11.50850
11.52325	H1	21
	V2	22	11.53800
11.55275	H2	23
	V1	24	11.56750
11.58225	H1	25
	V2	26	11.59700
11.61175	H2	27
	V1	28	11.62650
11.64125	H1	29
	V2	30	11.65600
11.67075	H2	31
	V1	32	11.68550


Astra 1B's EIRP (H polarization mode 1)


Astra 1B's EIRP (H polarization mode 2)


Astra 1B's EIRP (V polarization mode 1)


Astra 1B's EIRP (V polarization mode 2)


 Astra 1C

General

Designation	22653 / 93031A
Launch date	12 May 1993
Country of origin	Luxemburg
Mission	Direct TV
Geostationary orbit	19.2°E
Launch vehicle	Ariane V56

Tests were carried out in 14.5°E slot.

Technical data

EIRP coverage (dBW)

Horizontal polarization mode 1

Horizontal polarization mode 2

Vertical polarization mode 1

Vertical polarization mode 2

Specifications

Prime contractor	Hughes
Platform	HS-601
Mass at launch	2700 kg
Dimension	2.3 x 2.5 x 2.5 m
Stabilization	3 axis
DC power	BOL: 3500 W
Design lifetime	14 years
Beacon	11.44850 vertical 11.45100 horizontal
Ku-band (10.9-11.2 GHz)

Main transponders	18
Backup transponders	6
Power	63 W
Bandwidth	27 MHz
Coverage	Europe
EIRP	52.5 dBW
Polarization	linear
Uplink	13.0-13.25 GHz

Backup for Astra 1A

Transponder frequency chart (GHz)

Horizontal Downlink	Beam	Channel	Vertical Downlink
10.96425	H1	33
	V2	34	10.97900
10.99375	H2	35
	V1	36	11.00850
11.02325	H1	37
	V2	38	11.03800
11.05275	H2	39
	V1	40	11.06750
11.08225	H1	41
	V2	42	11.09700
11.11175	H2	43
	V1	44	11.12650
11.14125	H1	45
	V2	46	11.15600
11.17075	H2	47
	V1	48	11.18550
10.92075	H2	63
	V1	64	10.93550


Astra 1C's EIRP (H polarization mode 1)


Astra 1C's EIRP (H polarization mode 2)


Astra 1C's EIRP (V polarization mode 1)


Astra 1C's EIRP (V polarization mode 2)


 Astra 1D

General

Designation	23331 / 94070A
Launch date	1 Nov 1994
Country of origin	Luxemburg
Mission	Direct TV
Geostationary orbit	19.2°E
Launch vehicle	Ariane V69
Technical data

EIRP coverage (dBW)

Horizontal polarization mode 1

Horizontal polarization mode 2

Vertical polarization mode 1

Vertical polarization mode 2

Specifications

Prime contractor	Hughes
Platform	HS-601
Mass at launch	2924 kg
Dimension	2.3 x 2.5 x 2.5 m
Solar array	21 m span
Stabilization	3 axis
DC power	BOL: 3500 W
Design lifetime	13 years
Beacon	11.44750 vertical 11.45200 horizontal

Launched with the PVA (Perigee Velocity Augmentation) technic: initial parameters were 199.4/31123 km.

Ku-band (10.7-10.95 GHz)

Main transponders	14
Backup transponders	6?
Power	63 W
Bandwidth	26 MHz
Coverage	Europe
EIRP	52 dBW
Polarization	linear
Uplink	12.75-13.0 GHz
Ku-band (11.7-12.1 GHz), Astra 1E backup

Main transponders	4
Backup transponders	18
Power	63 W
Bandwidth	33 MHz
Coverage	Europe
EIRP	52 dBW
Polarization	linear
Uplink	17.3-17.7 GHz

+ Backup for Astra 1B & 1C

Transponder frequency chart (GHz)

Horizontal Downlink	Beam	Channel	Vertical Downlink
10.74125	H1	49
	V2	50	10.72900
10.74375	H2	51
	V1	52	10.75850
10.77325	H1	53
	V2	54	10.78800
10.80275	H2	55
	V1	56	10.81750
10.83225	H1	57
	V2	58	10.84700
10.86175	H2	59
	V1	60	10.87650
10.89125	H1	61
	V2	62	10.90600
10.92075	H2	63
	V1	64	10.93550
11.71950	H2	65
	V1	66	11.73900
11.75850	H2	67
	V1	68	11.77800


Astra 1D's EIRP (H polarization mode 1)


Astra 1D's EIRP (H polarization mode 2)


Astra 1D's EIRP (V polarization mode 1)


Astra 1D's EIRP (V polarization mode 2)


 Astra 1E

General

Designation	23686 / 95055A
Launch date	19 Oct 1995
Country of origin	Luxemburg
Mission	Direct TV
Geostationary orbit	19.2°E
Launch vehicle	Ariane V79

Cost (launch, satellite and insurance): $320 million

Technical data

EIRP coverage (dBW)

Horizontal polarization mode 1

Horizontal polarization mode 2

Vertical polarization mode 1

Vertical polarization mode 2

Specifications

Prime contractor	Hughes
Platform	HS-601
Mass at launch	3000 kg
Dimension	4.5 x 3.4 x 2.8 m
Solar array	26.2 m span
Stabilization	3 axis
DC power	BOL: 5500 W EOL: 4700 W
Design lifetime	14 years
Beacon	11.20200 GHz vertical 10.94850 GHz horizontal
Ku-band (11.7-12.1 GHz)

Main transponders	18
Backup transponders	6
Power	85 W
Bandwidth	33 MHz
Coverage	Europe
EIRP	52 dBW
Polarization	linear
Uplink	17.3-17.7 GHz

+ backup for Astra 1B, 1C & 1D

Transponder frequency chart (GHz)

Horizontal Downlink	Beam	Channel	Vertical Downlink
11.71950	H1	65
	V2	66	11.73900
11.75850	H2	67
	V1	68	11.77800
11.79750	H1	69
	V2	70	11.81700
11.83650	H2	71
	V1	72	11.85600
11.87550	H1	73
	V2	74	11.89500
11.91450	H2	75
	V1	76	11.93400
11.95350	H1	77
	V2	78	11.97300
11.99250	H2	79
	V1	80	12.01200
12.03150	H2	81
	V1	82	12.05100


Astra 1E's EIRP (H polarization mode 1)


Astra 1E's EIRP (H polarization mode 2)


Astra 1E's EIRP (V polarization mode 1)


Astra 1E's EIRP (V polarization mode 2)


 Astra 1F

General

Designation
Launch date	planned in March 1996
Country of origin	Luxemburg
Mission	Direct TV
Geostationary orbit	19.2°E
Launch vehicle	Proton
Launch site	Tyuratam
Technical data

Specifications

Prime contractor	Hughes
Platform	HS-601
Mass at launch	3010 kg
Mass in orbit	1800 kg
Dimension	2.3 x 2.5 x 2.5 m
Solar array	26 m span
Stabilization	3 axis
DC power	BOL: 4700 W
Design lifetime	13 years
Beacon	11.20100 vertical 10.94650 horizontal
Ku-band (12.1-12.5 GHz)

Main transponders	20 or 22?
Backup transponders	8
Power	82 W
Bandwidth	33 MHz
Coverage	Europe
EIRP	52 dBW
Polarization	linear
Uplink	17.7-18.1 GHz

+ backup for Astra 1A & 1E


 Astra 1G

General

Designation
Launch date	mid-1997
Country of origin	Luxemburg
Mission	Direct TV
Geostationary orbit	19.2°E
Launch vehicle
Launch site
Technical data

Specifications

Prime contractor	Hughes
Platform	HS-601HP
Mass at launch
Mass in orbit
Length
Width
Height
Solar array	gallium arsenide
Stabilization	3 axis
DC power	8000 W
Design lifetime	15 years
Beacon

Uses a new aerial design consisting of 2 ultra lightweight reflectors using Hughes' proprietary Contured Surface Technonlogy. Instead of conventional chemical rocket motors, Astra 1G incorporates a Xenon ion-drive for high power and reduced launch weight.

Ku-band (12.5-12.75 GHz)

Main transponders	16
Backup transponders
Power	100 W (TWTA)
Bandwidth	26 MHz
Coverage
EIRP	52 dBW
Polarization
Uplink	?
Ku-band (11.7-12.5 GHz), backup for Astra 1E & 1F

Main transponders	40: 18 for 1E and 22 for 1F
Backup transponders
Power	100 W (TWTA)
Bandwidth	33 MHz
Coverage
EIRP	52 dBW
Polarization
Uplink	17.3-18.1 GHz


 Astra 1H

General

Designation
Launch date	1998
Country of origin	Luxemburg
Mission	Direct TV
Geostationary orbit	19.2°E
Launch vehicle
Launch site

Backup of the 1A or 1E to 1G satellites

Technical data

Specifications

Prime contractor	Hughes
Platform	HS-601HP
Mass at launch
Mass in orbit
Length
Width
Height
Solar array	gallium arsenide
Stabilization	3 axis
DC power	8000 W
Design lifetime	15 years

Uses a new aerial design consisting of 2 ultra lightweight reflectors using Hughes' proprietary Contured Surface Technonlogy. Instead of conventional chemical rocket motors, Astra 1G incorporates a Xenon ion-drive for high power and reduced launch weight.

28 transponders powered by 100 W TWTA.


 Astra 2A

Astra 2A was intended to replace 1A after its lifecycle but it will probably start a new hotbird position, maybe at 28.2°E


 Astrid

General

Designation	23464 / 95002B
Launch date	24 Jan 1995 at 03:54 UT
Country of origin	Sweden
Operator	Swedish Space Corporation
Mission	Scientific: ionosphere and magnetosphere study
Perigee/Apogee	968/1023 km
Inclination	82.9°
Period	105 min
Launch vehicle	Cosmos 3M
Launch site	Plesetsk LC132

The satellite will initially be controlled from Swedish Space Corporation's ground station at ESRANGE in Kiruna in Northern Sweden. Thereafter control will be taken from Esrange, by the Swedish Institute of Space Physics in Kiruna.

The payload, which will emphasize studies of energetic neutral particles in the Earth's magnetosphere, includes PIPPI, the neutral particle imager; MIO, the miniature UV imaging system (with optical, UV continuum and Lyman alpha monitors) and EMIL, an electron spectrometer.

End of life

Out of service	Mar 1995
Cause	short circuit
Decay
Technical data

Specifications

Prime contractor	Platform: Swedish Space Corporation's Science Systems Division in Solna Payload: Swedish Institute of Space Physics in Kiruna
Platform	Freja C
Mass at launch	28 kg
Mass in orbit
Length	0.45 m
Width	0.45 m
Height	0.4 m
Solar array	4 wings, silicon
Stabilization	spin stabilized
DC power	28 V +-4v
Design lifetime	3 months
UHF-band (400.55 MHz)

Main transponders	1
Backup transponders	0
Power	2 W
Bandwidth	50 kHz
Coverage	omnidirectional
EIRP	-12-0 dB
Polarization	RHCP
Data flow	8 kbps
S-band (2208.629 MHz)

Main transponders	1
Backup transponders	0
Power	2 W
Bandwidth	890 kHz
Coverage	omnidirectional
EIRP	-6- 2 dB
Polarization	RHCP
Data flow	128 kbps


 Program: Astro

Astronomy Japanese program


Program: Astro

Astro A

Astro B

Astro C

Astro D

Astro E


 Astro A

Also called Hinotori

General

Designation	12307 / 81017A
Launch date	21 Feb 1981
Country of origin	Japan
Mission	Scientific: Sun study
Perigee/Apogee	573/639 km
Inclination	31.3°
Period	96.7 min
Launch vehicle	Mu 3S1
Launch site	Kagoshima
Mass at launch	195 kg
End of life

Decay	11 Jul 1991


 Astro B

Also called Tenma

General

Designation	13829 / 83011A
Launch date	20 Feb 1983
Country of origin	Japan
Mission	Scientific: X-ray astronomy
Perigee/Apogee	431/438 km
Inclination	31.5°
Period	93.3 min
Launch vehicle	Mu 3S1
Launch site	Tanegashima
Mass at launch	220 kg
End of life

Decay	17 Dec 1988


 Astro C

Also called Ginga

General

Designation	17480 / 87012A
Launch date	5 Feb 1987
Country of origin	Japan
Mission	Scientific: X-ray astronomy
Perigee/Apogee	395/450 km
Inclination	31°
Period	93 min
Launch vehicle	Mu 3S 2
Launch site	Kagoshima
Mass at launch	420 kg
End of life

Decay	1 Nov 1991


 Astro D

Also called Asuka or ASCA (Advanced Satellite for Cosmology and Astrophysics)

General

Designation	22521 / 93011A
Launch date	20 Feb 1993 at 02:00 UT
Country of origin	Japan
Operator	ISAS
Mission	Scientific: X-ray astronomy
Perigee/Apogee	538/645 km
Inclination	31.1°
Period	96.5 min
Launch vehicle	Mu 3S 2
Launch site	Kagoshima
Mass at launch	420 kg

Built by Nagoya's university and the Goddard Space Flight Center. Is equipped with 4 focal mirrors of 3.5 m and CCD detectors. The sensitiveness should be 100 times greater than HEAO 2.

First truly telescopic telecope in space and first Japanese X-ray imaging telescope (its previous X-ray satellites have carried x-ray detectors without focussing optics).

It carries CCD detectors and an imaging proportional counter. The spacecraft is sensitive to the 0.5-12 keV energy range. The Asuka telescope has a 30 arcmin field of view and 2 arcmin spatial resolution.


 Astro E

planned to be launched in 1999 by Mu-5


 Program: Astrolink

(15 Oct 1995)

Lockheed Martin announced its intention to expand its global telecommunications business.  In an application submitted to the Federal Communications Commission (FCC) last week, the Corporation filed its plans to construct, launch, and operate a global communication satellite system, called Astrolink(TM/SM).

Lockheed Martin said it would proceed with the system after obtaining regulatory approval, strategic alliance commitments and external investment.  The Astrolink system will offer a broad array of digital communications services, including voice, data, and video, to meet the needs of the U.S. and international marketplace in the 21st century.

"This project reflects our commitment to the commercial space business and expands our role in the growing telecommunications services market," said Vance D. Coffman, president and chief operating officer of Lockheed Martin's Space & Strategic Missiles Sector.  "Our background in advanced satellite technology, information networks, global systems and supporting ground systems makes Lockheed Martin uniquely qualified in a project of this magnitude and complexity."  Coffman said Lockheed Martin will vigorously seek domestic and international partners and investors in the $4 billion project.

In its FCC application, the Corporation detailed plans for a global satellite network using a constellation of nine geostationary satellites located in five separate orbit positions and connected by intersatellite links.  Astrolink(TM/SM) will use Ka-band frequencies and will offer affordable, high-data rate, digital communications services to businesses and common carrier providers world-wide.


 Astron

General

Designation	13901 / 83020A
Launch date	23 Mar 1983
Country of origin	CIS
Mission	Scientific: astronomy
Perigee/Apogee	25731/178615 km
Inclination	34.1°
Period	5932.2 min
Launch vehicle	Proton #106
Mass at launch	3500 kg (450 kg of instruments)

Carries the French and Russian experiment UFT for UV astronomy. Payload: 1 telescope (80 cm diameter and 5 m long) and a spectrometer (1.15-3.5 µm)


 Program: ATS

Application Technology Satellite

American multipurpose satellites designed to test new space instruments and demonstrate new satellite technologies.


Program: ATS

ATS 1

ATS 3

ATS 5

ATS 6


 ATS 1

General

Designation	02608 / 66110A
Launch date	7 Dec 1966
Country of origin	United States
Mission	Meteorology and communication experimentation
Geostationary orbit	149°W
Launch vehicle	Atlas Agena D

Transmitted the first high resolution photos of the Earth. It also relayed color television across the U.S. and was the first satellite to permit two-way VHF communication between ground and aircraft in flight.

End of life

Out of service	yes
Technical data

Transmits on 137.35 MHz (weak signal)


 ATS 3

General

Designation	03029 / 67111A
Launch date	5 Nov 1967
Country of origin	United States
Mission	Meteorology experimentation
Geostationary orbit	see below
Launch vehicle	Atlas Agena D
Launch site	Cape Canaveral

Carried advanced communications, meteorology, and navigation experiments. Provided the first color pictures of the Earth and proved the interest of maritime communications via satellite. Transmitted the first space communication between an Earth station and a plane on 21 Nov 1967 above the Atlantic.

Since 1980 the satellite transmit data to and from Antartica, especially the Internet.

Location

Begin	End	Position
L: 5 Nov 1967		47°W
Jun 1988	...	105°W
Oldest satellite still station keeping

Technical data

Transmits on 136.37 and 137.35 MHz (weak signals) or 135.555-135.650 MHz


 ATS 5

General

Designation	04068 / 69069A
Launch date	12 Aug 1969
Country of origin	United States
Mission	Telecommunications experimentation
Geostationary orbit
Launch vehicle
Launch site	Cape Canaveral

Provided data on auroran phenomenons and propagation in ionosphere.

End of life

Out of service	yes


 ATS 6

General

Designation	07318 / 74039A
Launch date	30 May 1974
Country of origin	United States
Mission	Telecommunications
Geostationary orbit	95°W
Launch vehicle
Launch site	Cape Canaveral
Mass at launch	930 kg

Numerous telecommunications experiments were carried out. With the satellite's 9 m antenna only small Earth antennas were needed. Scholar TV was provided to american children in the Rockies and Alaska. It was also used by SITE (Satellite Instructional Television Experiment) in 1975 to try and solve educational problems of India (half success). It also enabled communications between 2 unmanned spacecrafts.

End of life

Out of service	30 Jun 1979


 Aura

Also called D2B

General

Designation	08332 / 75092A
Launch date	27 Sep 1975
Country of origin	France
Mission	Scientific: astronomy
Perigee/Apogee	476/697 km
Inclination	37.1°
Period	96.5 min
Launch vehicle	Diamant #12
Mass at launch	120 kg
End of life

Out of service	28 Dec 1976
Cause	Stopped transmitting
Decay	30 Sep 1982


 Program: Auréole

French scientific program


Program: Auréole

Auréole 1

Auréole 2

Auréole 3


 Auréole 1

General

Designation	05729 / 71119A
Launch date	27 Dec 1971
Country of origin	France
Mission	Scientific: ionosphere study
Perigee/Apogee	388/1954 km
Inclination	74°
Period	108.8 min
Launch vehicle
Launch site	Plesetsk


 Auréole 2

General

Designation	07003 / 73107A
Launch date	26 Dec 1973
Country of origin	France
Mission	Scientific: ionosphere study
Perigee/Apogee	387/1441 km
Inclination	74°
Period	103.3 min
Launch vehicle
Launch site	Plesetsk


 Auréole 3

General

Designation	12848 / 81093A
Launch date	21 Sep 1981
Country of origin	France
Mission	Scientific: ionosphere and magnetosphere study
Perigee/Apogee	394/1672 km
Inclination	82.5°
Period	105.8 min
Launch vehicle	Cyclone 3
Launch site	Plesetsk


 Program: Aurora

Telecommunication program operated by Alascom Inc. a subsidiary of Pacific Telecom.

Contact

Alascom Inc.

210 Bluff Road, Box 6607, Anchorage, AK99502-7649, USA

Tel: +1-907-264-7000

Fax: +1-907-264-7704


Program: Aurora

Aurora 1

Aurora 2


Aurora's specifications

Prime contractor	GE Astro Space
Platform	GE 3000
Mass in orbit	760 kg
Dimension	1.63 x 1.32 x 0.99 m
Stabilization	3 axis
DC power	BOL: 1400 W
Design lifetime	1: 10 years 2: 12 years


Aurora_1
 Aurora 1

Also called Satcom 5

General

Designation	13631 / 82105A
Launch date	28 Oct 1982
Country of origin	United States
Mission	Telecommunications
Geostationary orbit	see below
Launch vehicle	Thor Delta #165
Mass at launch	1084 kg
Location

Begin	End	Position
L: 28 Oct 1982		139°W
1992?		143°W
Feb 1995	...	105°W
Technical data

Specifications

C-band

Main transponders	24
Backup transponders	4
Power	8.5 W (SSPA)
Bandwidth	36 MHz
Coverage
EIRP	34 dBW
Polarization	linear


 Aurora 2

Also called Satcom C5

General

Designation	21392 / 91037A
Launch date	29 May 1991
Country of origin	United States
Mission	Telecommunications
Geostationary orbit	139°W
Launch vehicle	Delta 2 #205
Mass at launch	1338 kg
Technical data

Specifications

C-band transponder frequency chart

C-band

Main transponders	24
Backup transponders	8
Power	11 W (SSPA)
Bandwidth	36 MHz
Coverage	Odd transponders to the United States Even transponders to Alaska and Canada
EIRP	34 dBW
Polarization	linear


 Program: Ayame

Means "iris"

Also called ECS (Experimental Communication Satellite)

Japanese telecommunication program


Program: Ayame

Ayame 1

Ayame 2


 Ayame 1

Also called ECS 1

General

Designation	11261 / 79009A
Launch date	6 Feb 1979
Country of origin	Japan
Mission	Telecommunications, experimental
Perigee/Apogee	29259/37424 km
Inclination	4.9°
Period	1313 min
Launch vehicle	N1
Launch site	Tanegashima
Mass at launch	130 kg
End of life

Out of service	After 20 min (or 3 days?)


 Ayame 2

General

Designation	11715 / 80018A
Launch date	22 Feb 1980
Country of origin	Japan
Mission	Telecommunications, experimental
Perigee/Apogee	32785/36839 km
Inclination	1.4°
Period	1386.6 min
Launch vehicle	N1
Launch site	Tanegashima
Mass at launch	130 kg
End of life

Out of service	After launch


 Azur

Also called GRS A

General

Designation	04221 / 69097A
Launch date	8 Nov 1969
Country of origin	Germany
Mission	Scientific: ionosphere study
Perigee/Apogee	373/2118 km
Inclination	102.7°
Period	110.4 min
Launch vehicle	Scout #67
Mass at launch	72 kg

Studies aurora borealis, Earth's radiation belt and charged particles from the Sun.


 Badr A

General

Designation	20685 / 90059A
Launch date	16 Jul 1990
Country of origin	Pakistan
Mission
Perigee/Apogee	208/988 km
Inclination	28.5°
Period	96.7 min
Launch vehicle	Long March 2E
Launch site	Xichang
End of life

Decay	8 Dec 1990


 Program: Bhaskara

Indian program named from a Indian mathematician and astronomer.


Program: Bhaskara

Bhaskara 1

Bhaskara 2


 Bhaskara 1

General

Designation	11392 / 79051A
Launch date	7 Jun 1979
Country of origin	India
Mission	Remote sensing
Perigee/Apogee	394/399 km
Inclination	50.7°
Period	92.5 min
Launch vehicle	Intercosmos
Launch site	Kapustin Yar
Mass at launch	444 kg
End of life

Decay	17 Feb 1989


 Bhaskara 2

General

Designation	12968 / 81115A
Launch date	20 Nov 1981
Country of origin	India
Mission	Remote sensing
Perigee/Apogee	368/372 km
Inclination	50.6°
Period	92 min
Launch vehicle	Intercosmos
Launch site	Kapustin Yar
Mass at launch	436 kg
End of life

Decay	30 Nov 1991


 Program: Brazilsat

Also called SBTS (Sistema Brasileiro de Telecomunicacoes por Satellite)

Brazilian telecommunication system operated by Embratel.

Contract for Brazilsat As was worth $122.5 million for construction. Contract for Brazilsat Bs was worth $175.2 million for construction.

Contact

Embratel (Empresa Brasileira de Telecomunicações S.A.)

Avenida Presidente Vargas 1012, Rio de Janeiro 20279-900, Brazil

Tel: +55-21-216-7535

Fax: +55-21-216-8831


Program: Brazilsat

Brazilsat A1	Brazilsat A2
Brazilsat B1	Brazilsat B2	Brazilsat B3


Brazilsat A's specifications

Prime contractor	Spar Aerospace
Platform	HS-376
Mass at launch	1140 kg
Mass in orbit	671 kg
Diameter	2.19 m
Height	7.09 m deployed
Stabilization	Spin stabilized
DC power	BOL: 982 W EOL: 799 W
Design lifetime	1: 9 years 2: 11 years


Brazilsat A's C-band

Main transponders	26
Backup transponders	6
Power	10 W (TWTA)
Bandwidth	36 MHz
Coverage	Brazil and neighboring countries
EIRP	36 dBW
Polarization	linear


Brazilsat B's specifications

Prime contractor	Hughes
Platform	HS-376W
Mass at launch	1760 kg
Mass in orbit
Dry mass	800 kg
Diameter	3.64 m
Height	3.64 m, 8.38 m deployed
Stabilization	spin stabilized
DC power	BOL: 1650 W
Design lifetime	12 years
Apogee motor	Thiokol Star 30 (solid fuel)


Brazilsat B's C-band

Main transponders	28
Backup transponders
Power	15 W
Bandwidth	31 MHz
Coverage	Brazil and South-America
EIRP	38 dBW
Polarization


Brazilsat B's X-band

Main transponders	1
Backup transponders
Power
Bandwidth
Coverage
EIRP
Polarization


Brazilsat B's C-band frequency chart
 Brazilsat B's C-band frequency chart (GHz)

Horizontal Uplink	Horizontal Downlink	Channel	Vertical Downlink	Vertical Uplink
	3.641	#1AE		?
?		#1AE	3.660
	3.680	#2AE		?
?		#2AE	3.700
	3.720	1		5.945
5.965		2	3.740
	3.760	3		5.985
6.005		4	3.780
	3.800	5		6.025
6.045		6	3.820
	3.840	7		6.065
6.085		8	3.860
	3.880	9		6.105
6.125		10	3.900
	3.920	11		6.145
6.125		12	3.940
	3.960	13		6.185
6.205		14	3.980
	4.000	15		6.225
6.245		16	4.020
	4.040	17		6.265
6.285		18	4.060
	4.080	19		6.305
6.325		20	4.100
	4.120	21		6.345
6.365		22	4.140
	4.160	23		6.385
6.405		24	4.180


 Brazilsat A1

Also called SBTS A1

General

Designation	15561 / 85015B
Launch date	8 Feb 1985
Country of origin	Brazil
Mission	Telecommunications
Geostationary orbit	see below
Launch vehicle	Ariane V12
Location

Begin	End	Position
L: 8 Feb 1985		65°W
late-1994		63°W, inclined

Sold to HCI in October 1995. The antenna was re-aimed to North America.

Technical data

Specifications

C-band

Transponder frequency chart


 Brazilsat A2

Also called SBTS A2

General

Designation	16650 / 86026B
Launch date	28 Mar 1986
Country of origin	Brazil
Mission	Telecommunications
Geostationary orbit	see below
Launch vehicle	Ariane V17
Location

Begin	End	Position
L: 28 Mar 1986		70°W
late-1994	Jun 1995	65°W
Aug 1995		92°W
Technical data

Specifications

C-band

Transponder Frequency Chart


 Brazilsat B1

Also called SBTS B1

General

Designation	23199 / 94049A
Launch date	10 Aug 1994
Country of origin	Brazil
Mission	Telecommunications
Geostationary orbit	70°W
Launch vehicle	Ariane V66

Cost: $140 million

Technical data

Specifications

C-band

X-band

C-band transponder frequency chart


 Brazilsat B2

Also called SBTS B2

General

Designation	23536 / 95016A
Launch date	28 Mar 1995
Country of origin	Brazil
Mission	Telecommunications
Geostationary orbit	65°W
Launch vehicle	Ariane V71

Cost: $125 million

Technical data

Specifications

C-band

X-band

C-band transponder frequency chart


 Brazilsat B3

Also called SBTS B3

General

Designation
Launch date	planned in late 1997
Country of origin	Brazil
Mission	Telecommunications
Geostationary orbit	61°W
Launch vehicle	Ariane

Cost: $70 million agreement (without launch?) This is an amendment to the Brasilsat B contract with Hughes signed in 1990, which gave EMBRATEL options for additional spacecraft.

Technical data

Specifications

C-band

C-band transponder frequency chart

No X-band payload: the C-band only spacecraft will provide nearly 20 percent higher signal power than the 2 Brazilsat B's. It will have one C-band beam for national service, and a second C-band regional beam that will focus higher power on the major urban areas.


 Bremsat

General

Designation	22998 / 94006H
Launch date	3 Feb 1994
Country of origin	Germany
Operator	ZARM, University of Bremen
Mission	Scientific: high atmosphere study
Perigee/Apogee	344/363 km
Inclination	56.9°
Period	91.4 min
Launch vehicle	STS 60
Mass at launch	63 kg

Measured heat conductivity, micrometeorites, and the density of the upper atmosphere.

End of life

Decay	12 Feb 1995


 Program: BSAT

Japanese telecommunication program operated by NHK

2 satellites (1A & 1B) to be launched in 97 and 98 by Ariane

They will replace the Yuri Direct TV satellites

Specifications

Prime contractor	Hughes
Platform	probably an HS-376
Mass at launch	1250 kg
Mass in orbit	~ 600 kg
Dimension
Solar array
Stabilization
DC power
Design lifetime	10 years
Ku-band (wideband)

Main transponders	1
Backup transponders
Power	120 W (TWTA)
Bandwidth	60 MHz
Coverage
EIRP
Polarization	circular
Ku-band (TV)

Main transponders	3
Backup transponders
Power	20 W (SSPA)
Bandwidth	27 MHz
Coverage
EIRP
Polarization	circular
Frequencies

Uplink	14.2-14.3 GHz
Downlink	11.9-12.0 GHz


 Program: BSB

English direct TV program abandonned in 1992. The satellites were ordered by BSB which merged with Sky TV giving BSkyB.


Program: BSB

BSB 1

BSB 2


BSB's specifications

Prime contractor	Hughes
Platform	HS-376
Mass at launch	1250 kg
Mass in orbit	660 kg
Payload mass	100 kg: transponders: 90 kg, antennas: 10 kg
Diameter	2.16 m
Height	4.8 m
Stabilization	Spin stabilized
DC power	BOL: 1024 W
Design lifetime	10 years
Beacon	12.494 or 12.495 GHz

Equipped with steerable antennas


BSB's Ku-band

Main transponders	5
Backup transponders	1
Power	2 x 55 W (TWTA)
Bandwidth	27 MHz
Coverage
EIRP	59 dBW
Polarization	circular R
Frequencies	Uplink: 17.3-17.6 GHz Downlink: 11.786-12.091 GHz


 BSB 1

Also called Marco Polo 1

General

Designation	20193 / 89067A
Launch date	27 Aug 1989
Country of origin	United Kingdom
Mission	Direct TV
Geostationary orbit	see below
Launch vehicle	Thor Delta #187

Stopped transmitting on 31 Dec 1992 and became Sirius 1 in 1994.

Location

Begin	End	Position
L: 27 Aug 1989
Nov 1991	Dec 1992	31°W
1994	...	Sirius 1
Technical data

Specifications

Ku-band


 BSB 2

Also called Marco Polo 2

General

Designation	20762 / 90074A
Launch date	18 Aug 1990
Country of origin	United Kingdom
Mission	Direct TV
Geostationary orbit	see below
Launch vehicle	Delta 2 #198

Was sold in September 1992 and became Thor.

Location

Begin	End	Position
L: 18 Aug 1990
	Aug 1992	31°W
Sep 1992	...	Thor
Technical data

Specifications

Ku-band


 Castor

Also called D5B

General

Designation	07802 / 75039B
Launch date	17 May 1975
Country of origin	France
Mission	Scientific: geodesy
Perigee/Apogee	277/1275 km
Inclination	29.9°
Period	100.3 min
Launch vehicle	Diamant #11
Mass at launch	76 kg

Tests a high precision micro-acceleratometer.

It is the counterpart of the first Castor that was lost with Pollux on 22 May 1973.

End of life

Decay	18 Feb 1979


 Caribstar

Also called CariBSS

General

Designation
Launch date	planned in mid-1999
Country of origin	United States
Mission	Telecommunications
Geostationary orbit	120°W
Launch vehicle	Ariane
Technical data

Specifications

L-band


 Program: Cat

European micro satellite program for experimentation


Program: Cat

Cat 1

Cat 2

Cat 3

Cat 4


 Cat 1

General

Designation	11645 / 79104A
Launch date	24 Dec 1979
Country of origin	Europe
Mission	Technology experimentation
Perigee/Apogee	125/14047 km
Inclination	17.8°
Period	259.1 min
Launch vehicle	Ariane L01
End of life

Decay	27 Nov 1989


 Cat 2

End of life

Out of service	23 May 1980
Cause	Launch failure of Ariane L02


 Cat 3

General

Designation	12546 / 81057C
Launch date	19 Jun 1981
Country of origin	Europe
Mission	Technology experimentation
Perigee/Apogee	227/29240 km
Inclination	10.6°
Period	508.8 min
Launch vehicle	Ariane L03
End of life

Out of service	96 hours after launch


 Cat 4

Also called Thésée

General

Designation	13011 / 81122B
Launch date	20 Dec 1981
Country of origin	Europe
Mission	Scientific
Perigee/Apogee	219/38645 km
Inclination	63.8°
Period	534.3 min
Launch vehicle	Ariane L04

Measures the Sun light

End of life

Out of service	9 Jan 1982
Cause	Stopped transmitting


 Program: CBERS

China/Brazil Earth Resources Satellite

Joint venture to launch 2 satellites for remote monitoring of the environment related to agriculture, oceanography and geology. The Brazilian government has suggested to China that another two 1400-kilogram satellites should be developed.

The two satellites will be assembled in China with parts manufactured in both countries and Brazil will invest 60 million dollars, covering 30% of the costs of the project. The two countries started manufacturing the two satellites in 1988 but the project was delayed by a budget shortfall on the Brazilian side (satellites were planned for 1994 & 1995).

The Brazilian Ministry of the Environment will use the two new satellites in the Amazon Integrated Program, created to develop the Amazon region based on sustained development policies.

2 follow-on satellites are also planned


 CBERS 1

General

Designation
Launch date	planned in Oct 1997
Country of origin
Mission	Remote sensing
Perigee/Apogee	heliosynchronous orbit, 778 km
Inclination
Period	repeat period: 20 days
Launch vehicle	Long March
Launch site
Technical data

Specifications

Prime contractor
Platform
Mass at launch	1400 kg
Mass in orbit
Dimension	1.8 x 1.9 m
Solar array	8.3 x 3.3 m
Stabilization	3 axis
DC power
Design lifetime
5-channel linear CCD detector (visible, IR, panchromatic)

Wavebands	0.59-0.89 µm 0.5-12.9 µm
Swath width	120 km
Resolution	Visible: 19 m IR: 80 m
Wide-field imager

Resolution	260 m
Swath width	900 km


 Cerise

General

Designation	23606 / 95033B
Launch date	7 Jul 1995
Country of origin	France
Mission	Military: ELINT
Perigee/Apogee	666/675 km
Inclination	98.2°
Period	98.2 min
Launch vehicle	Ariane V75

Operated by CNES and the DGA (Délégation Générale de l'Armement), ministry of defense. Cerise is to catalog terrestrial electromagnetic sources between 500 MHz and 20 GHz. Cost: FRF 87 million.

It will be followed by Clementine to be launched in 1997 to catalog source between 20 MHz and 1 GHz. (should cost FRF 90 million).

Technical data

Specifications

Prime contractor	Alcatel Espace & Thomson CSF
Platform	UoSAT
Mass at launch	50 kg
Mass in orbit
Length
Width
Height
Stabilization	3 axis
DC power
Design lifetime	2.5 years


 Chinastar 1

Lockheed Martin-built satellite for China (based on a A2100, astro space division). Lifetime: 15 years. To be launched by a Long March in the fall of 1997.

Operator: China Orient Telecom Satellite Co Ltd, an affiliate of the Ministry of Posts and Telecommunications

18 C-band transponders (45 W)

16 Ku-band transponders (all 85 W but 4 135 W)

coverage: china


Cluster
 Program: Cluster

European scientific program to be launched in 1996

Specifications

Prime contractor	Dornier
Platform
Mass at launch	1200 kg
Payload mass	72 kg
Propellant mass	650 kg
Dry mass	550 kg
Diameter	2.9 m
Height	1.3 m
Solar array
Stabilization	spin stabilized (15 rpm)
DC power	EOL: 224 W (80 Ah silver cadmium batteries)
Payload power	47 W
Design lifetime	2 years
Telemetry	2-262 kbps

Tape recorder capacity: 1 gbit

Frequencies

Cluster 1	2242.000 MHz
Cluster 2	2249.000 MHz
Cluster 3	2277.000 MHz
Cluster 4	2270.000 MHz
Payload

STAFF ( Spatio-Temporal Analysis of Field Fluctuations)

EFW (Electric Fields and Waves)

WHISPER (Waves of High frequency and Sounder for probing of density by Relaxation)

WBD (Wide Band Data)

DWP (Digital Wave Processor)

FGM (Fluxgate Magnetometer)

EDI (Electronic Drift Instrument)

CIS (Cluster Ion Spectrometry)

PEACE (Plasma Electron And Current Analyser)

RAPID (Research with Adaptive Particle Imaging Detectors)

ASPOC (Active Spacecraft Potential Control)


 Cobe

COsmic Background Explorer

General

Designation	20322 / 89089A
Launch date	18 Nov 1989
Country of origin	United States
Mission	Scientific: astronomy
Perigee/Apogee	872/886 km
Inclination	99°
Period	102.5 min
Launch vehicle	Thor Delta #189

Studies the thermical radiation of the sky (gave its precise temperature: 2.735 K).


 Program: Comstar

American telecommunication satellite program operated by Comsat. Capacity is leased to AT&T.

Contact

COMSAT Corporation

6560 Rock Spring Drive, Bethesda, MD 20817, USA

Tel: +1-301-214-3658

Fax: +1-301-214-7130

http://www.comsat.com


Program: Comstar

Comstar 1

Comstar 2

Comstar 3

Comstar 4


Comstar's specifications

Prime contractor	Hughes
Platform	HS 351 (same as Intelsat 4)
Mass at launch	1516 kg
Mass in orbit	911 kg
Dimension	2.5 m
Stabilization	Spin stabilized (56 rpm)
DC power	BOL: 570 W
Design lifetime	10 years

Equipped with two Ka-band beacons for propagation research (19 and 28.6 GHz).


Comstar's C-band

Main transponders	24
Backup transponders
Power	Horizontal: 5 W (TWTA) Vertical: 5.5 W (TWTA)
Bandwidth	36 MHz
Coverage	CONUS
EIRP	33 dBW
Polarization	linear H/V


 Comstar 1

General

Designation	08838 / 76042A
Launch date	13 May 1976
Country of origin	United States
Mission	Telecommunications
Geostationary orbit	128°W
Launch vehicle	Atlas Centaur
Launch site	Cape Canaveral
End of life

Out of service	yes
Technical data

Specifications

C-band


 Comstar 2

General

Designation	09047 / 76073A
Launch date	22 Jul 1976
Country of origin	United States
Mission	Telecommunications
Geostationary orbit	94°W
Launch vehicle	Atlas Centaur
Launch site	Cape Canaveral
End of life

Out of service	yes
Technical data

Specifications

C-band


 Comstar 3

General

Designation	10975 / 78068A
Launch date	29 Jun 1978
Country of origin	United States
Mission	Telecommunications
Geostationary orbit	87°W
Launch vehicle	Atlas Centaur
Launch site	Cape Canaveral
End of life

Out of service	yes
Technical data

Specifications

C-band


 Comstar 4

General

Designation	12309 / 81018A
Launch date	21 Feb 1981
Country of origin	United States
Mission	Telecommunications
Geostationary orbit	76°W, inclined
Launch vehicle	Atlas Centaur
Launch site	Cape Canaveral

Used for telephony and data transmission

Technical data

Specifications

C-band


 Corsa B

Also called Hakucho

General

Designation	11272 / 79014A
Launch date	21 Feb 1979
Country of origin	Japan
Mission	Scientific: X-ray astronomy
Perigee/Apogee	543/566 km
Inclination	29.8°
Period	95.7 min
Launch vehicle	Mu 3C
Launch site	Kagoshima
Mass at launch	96 kg
End of life

Decay	15 Apr 1985


 Cos B

COsmic ray Satellite

General

Designation	08062 / 75072A
Launch date	9 Aug 1975
Country of origin	Europe
Mission	Scientific: gamma-ray astronomy
Perigee/Apogee	442/99002 km
Inclination	90.3°
Period	2203.9 min
Launch vehicle	Thor Delta #113
Mass at launch	280 kg


page intentionally left blank


 Coupon 1

General

Designation
Launch date	planned in Oct 1994
Country of origin	CIS
Mission	Telecommunications
Geostationary orbit	55°E
Launch vehicle
Launch site

Would be operated by GIS: Global Information Systems

Technical data

made from the Prognoz 2nd generation platform

Ku-band

Main transponders	16
Backup transponders
Power
Bandwidth	36 MHz
Coverage	Europe and Asia, several spots
EIRP	50 dBW
Polarization	linear
Transponder frequency chart (GHz)

Horizontal Downlink	Transponder	Vertical Downlink
10.980
		10.980
11.060
		11.060
11.100
		11.100
11.180
		11.180
11.480
		11.480
11.560
		11.560
11.600
		11.600
11.680
		11.680


 Coupon 2

Launch planned in April 1995, slotted in 9.5°W


 Coupon 3

Launch planned in October 1995 slotted in 162°E


 Courier 1B

General

Designation	00058 / 60013A
Launch date	4 Oct 1960
Country of origin	United States
Mission	Telecommunications: recording satellite
Perigee/Apogee	967/1214 km
Inclination	28.3°
Period	107.1 min
Launch vehicle	Thor Ablestar
Launch site	Cape Canaveral

Could record messages from Earth station and rebroadcast them.


 CTA

General

Designation	22214 / 92070C
Launch date	22 Oct 1992
Country of origin	Canada
Mission
Perigee/Apogee	164/243 km
Inclination	28.4°
Period	88.4 min
Launch vehicle	STS 52
End of life

Cause	Retrieved by the Shuttle
Decay	1 Nov 1992


 CTS

Also called Hermès

General

Designation	08585 / 76004A
Launch date	17 Jan 1976
Country of origin	Canada
Mission	Telecommunications
Geostationary orbit	116°W
Launch vehicle	Thor Delta #119
Mass at launch	674 kg, 347 kg in orbit

Used by the United States and Canada for TV transmission tests with small Earth stations. Also used for computer links.

End of life

Out of service	November 1979


 Program: Dash

American program for radars calibration


 Program: DBS

American digital direct TV program operated by Hughes Communications Inc. (HCI).

Two companies provided TV programs: DirecTV a subsidiary of GM Hughes Electronics used 11 transponders (per satellite) while the 5 ones left were managed by USSB (United States Satellite Broadcasting) a division of Hubbard Broadcasting Inc. The receivers were first provided by Thomson Consumer Electronics (RCA trademark).

Contact

Hughes Communications Inc.

PO Box 92424, Los Angeles, CA 90009, USA

Tel: +1-800-824-8133

Tel: +1-310-607-4000

Fax: +1-310-607-4255

DirecTv

PO Box 92424, Los Angeles, CA 90009, USA

Tel: +1-818-569-7700

http://www.directv.com

USSB

3415 University Avenue, St Paul, NM 55114, USA

Tel: +1-612-646-5555

Fax: +1-612-642-4103


Program: DBS

DBS 1

DBS 2

DBS 3

DBS 4


DBS' specifications

Prime contractor	Hughes
Platform	HS-601S
Mass at launch	2930 kg
Mass in orbit	1700 kg
Dimension	2.27 x 2.27 x 2.27 m
Solar array	35.1 m span
Stabilization	3 axis
DC power	4500 W
Design lifetime	12 years

Transponders are optimized for digital TV: fixed gain and automatic level control.


DBS' Ku-band (12.2-12.7 GHz)

Main transponders	16
Backup transponders	8
Power	120 W (TWTA)
Bandwidth	24 MHz
Coverage	Continental US
EIRP	52 dBW
Polarization	LHCP

The system can be configured as 8 transponders with 240 W power to provide 2.9 dBW more.

The DSS architecture can broadcast 40Mbits/sec per transponder in either of two error control modes. In High mode, 30Mbps is allocated to information and 10Mbps to error control. In Low mode, 23Mbps is allocated to information and 17Mbps is allocated to error control.


DBS' EIRP

Add 2.9 dBW for transponders with 240 W power.


 DBS 1

General

Designation	22930 / 93078A
Launch date	18 Dec 1993
Country of origin	United States
Mission	Direct TV
Geostationary orbit	101.2°W
Launch vehicle	Ariane V62
Technical data

EIRP coverage (dBW)

Specifications

Ku-band

Uplink frequency: 17.3-18.8 GHz


 DBS 2

General

Designation	23192 / 94047A
Launch date	3 Aug 1994
Country of origin	United States
Mission	Direct TV
Geostationary orbit	100.8°W
Launch vehicle	Atlas Centaur

It carried a time capsule named SpaceArc containing messages from the vice-president of the U.S.A. (Al-Gore) and his predecessor. After its useful life span the spacecraft will be moved to a higher orbit so that only an explorer from a distant future generation may uncover the messages.

Technical data

EIRP coverage (dBW)

Specifications

Ku-band

Apogee motor: ARC490N (liquid fuel)


 DBS 3

General

Designation	23598 / 95029A
Launch date	10 Jun 1995
Country of origin	United States
Mission	Direct TV
Geostationary orbit	101°W
Launch vehicle	Ariane V74

Will be used ofr power enforcement

Technical data

EIRP coverage (dBW)

Specifications

Ku-band


 DBS 4

General

Designation
Launch date	planned in 1996
Country of origin	United States
Mission	Direct TV
Geostationary orbit	157°W
Launch vehicle	Atlas Centaur?


DBSC 1
 DBSC 1 & 2

Direct Broadcasting Satellite Corp. of Washington, DC

Company bought in Dec 1995 by Echostar

General

Designation
Launch date	1997?
Country of origin
Mission
Geostationary orbit
Launch vehicle
Launch site
Technical data

Specifications

Prime contractor	Lockheed Martin Astro Space
Platform	Astro Space A2100
Mass at launch
Mass in orbit
Length
Width
Height
Stabilization
DC power
Design lifetime	13.5 years


 Debut

General

Designation	20479 / 90013B
Launch date	8 Feb 1990
Country of origin	Japan
Mission
Perigee/Apogee	908/1742 km
Inclination	99°
Period	112.2 min
Launch vehicle
Launch site	Tanegashima


 Delta Star

Also called USA 036

General

Designation	19911 / 89026A
Launch date	24 Mar 1989
Country of origin	United States
Mission	Military
Perigee/Apogee	307/312 km
Inclination	47.7°
Period	90.7 min
Launch vehicle	Thor Delta #184

Part of the Star War program. Payload: radar, laser and 7 optical sensors (IR).

End of life

Decay	23 Jun 1992


 Denpa

Means "radio wave"

General

Designation	06152 / 72064A
Launch date	19 Aug 1972
Country of origin	Japan
Mission	Scientific: ionosphere study
Perigee/Apogee	238/6322 km
Inclination	31°
Period	157.4 min
Launch vehicle	Mu 4S
Launch site	Kagoshima
Mass at launch	75 kg
End of life

Decay	19 May 1980


 Program: DFS Kopernikus

Deutscher Fernmelde Satellit

German telecommunication program operated by DBP (Deutsche BundesPost)

Contact

Deutsche Bundespost Telekom

Godesberger Alle 87-91, 53175 Bonn, Germany

Tel: +49-228-181-1211

Fax: +49-228-181-8872


Program: DFS Kopernikus

DFS 1

DFS 2

DFS 3


DFS Kopernikus's specifications

Prime contractor	R-DFS consortium with ANT and MBB-ERNO
Platform	Spacebus 100
Mass at launch	1415 kg
Mass in orbit	850 kg
Payload mass	158 kg: transponders: 126 kg, antennas: 32 kg
Dimension	1.4 x 1.9 x 4.1 m
Solar array	15.4 m span
Stabilization	3 axis
DC power	BOL: 1990 W EOL: solstice: 1463 W, equinox: 1558 W
Payload power	896 W
Design lifetime	10 years
Capacity	1800 phone circuits and 200 data circuits


DFS Kopernikus's Ku-band

Main transponders	10
Backup transponders
Power	20 W (TWTA)
Bandwidth	3 transponders in 11 GHz: 90 MHz 7 transponders in 12 GHz: 44 MHz
Coverage	Germany
EIRP	49 dBW
Polarization	linear
Uplink	14.0-14.25 GHz for 11 GHz downlink 14.25-14.5 GHz for 12 GHz downlink


DFS Kopernikus's Ka-band

Main transponders	1
Backup transponders
Power	20 W (TWTA)
Bandwidth	90 MHz
Coverage	Germany
EIRP	48 dBW
Polarization
Uplink	29.5-29.6 GHz
Downlink	19.7-19.8 GHz


DFS Kopernikus's Transponder frequency chart (GHz)

Horizontal Downlink	Transponder	Vertical Downlink
11.475	A1
11.525	A2
	B1	11.550
	B2	11.600
11.625	C1
11.675	C2
	K1	12.524
12.559	K2
	K3	12.591
12.625	K4
	K5	12.658
12.692	K6
	K7	12.725


 DFS 1

General

Designation	20041 / 89041B
Launch date	5 Jun 1989
Country of origin	Germany
Mission	Telecommunications
Geostationary orbit	see below
Launch vehicle	Ariane V31
Location

Begin	End	Position
L: 5 Jun 1989
Jan 1991	Jan 1993	23.5°E
Jul 1993	Nov 1995	33.5°E

Ran out of control a few days in Nov 1995. Control was regained in early December but DFS 1 escaped again in mid-December 1995

End of life

Out of service	Nov 1995
Cause	satellite out of control
Technical data

Specifications

Ku-band

Ka-band

Transponder frequency chart

Beacon: 11.450 GHz vertical & 11.4535 GHz horizontal


 DFS 2

General

Designation	20706 / 90063B
Launch date	24 Jul 1990
Country of origin	Germany
Mission	Telecommunications
Geostationary orbit	28.5°E
Launch vehicle	Ariane V37
Technical data

Specifications

Ku-band

Ka-band

Transponder frequency chart

Beacon: 11.450 GHz vertical & 11.4535 GHz horizontal


 DFS 3

General

Designation	22175 / 92066A
Launch date	12 Oct 1992
Country of origin	Germany
Mission	Telecommunications
Geostationary orbit	23.5°E
Launch vehicle	Delta 2 #215
Technical data

EIRP Coverage (dBW)

Specifications

Ku-band

Ka-band

Transponder frequency chart


DFS Kopernikus 3's EIRP


 Program: Diadème

French scientific program: geodesy studies using laser and doppler effect


Program: Diadème

Diadème 1

Diadème 2


 Diadème 1

Also called D1C

General

Designation	02674 / 67011A
Launch date	8 Feb 1967
Country of origin	France
Mission	Scientific: geodesy
Operator	CNES
Perigee/Apogee	545/1083 km
Inclination	39.9°
Period	101.2 min
Launch vehicle	Diamant #3
Mass at launch	20 kg
End of life

Out of service	2 Jan 1970
Cause	Stopped broadcasting


 Diadème 2

Also called D1D

General

Designation	02680 / 67014A
Launch date	15 Feb 1967
Country of origin	France
Mission	Scientific: geodesy
Operator	CNES
Perigee/Apogee	586/1731 km
Inclination	39.4°
Period	108.5 min
Launch vehicle	Diamant #4
Mass at launch	20 kg
End of life

Out of service	16 Sep 1968 (stopped transmitting on 5 Apr 1967)


 Diapason

Also called D1A

General

Designation	02016 / 66013A
Launch date	17 Feb 1966
Country of origin	France
Mission	Scientific: geodesy
Operator	CNES
Perigee/Apogee	502/2484 km
Inclination	34.1°
Period	115.8 min
Launch vehicle	Diamant #2
Mass at launch	18.5 kg

Also used to test technology

End of life

Out of service	23 Jan 1972
Cause	Stopped transmitting


 Program: Discoverer

USAF program: 38 satellites launched between 28 Feb 1959 and 27 Feb 1962

It seems that all Discoverers beginning with number 14 are KH spysats. See Thor Agena listing for the launches.


 Program: DMSP

Defense Meteorological Satellite Program

USAF meteorology program. The technology was first tested by the AMS program.

All DMSP satellites were built by RCA Astro Space, which is now Lockheed Martin Astro Space; based on the Tiros N bus.

5 DMSP B5D3 have been ordered


Program: DMSP

DMSP B5D1-1 (76091A)

DMSP B5D1-2 (77044A)

DMSP B5D1-4 (79050A)

DMSP B5D2-3

DMSP B5D2-4 (88006A)

DMSP B5D2-5 (90105A)

DMSP B5D2-6 (91082A)

DMSP B5D2-7

DMSP B5D2-8


DMSP B5D1's specifications

Prime contractor	MM Astro Space
Platform
Mass at launch	between 450 & 513 kg
Mass in orbit
Diameter	1.68 m
Height	6.4 m
Solar array
Stabilization
DC power
Design lifetime


DMSP B5D2's specifications

Prime contractor	LM Astro Space
Platform	based on the Tiros N bus
Mass at launch	750 kg?
Mass in orbit
Diameter	1.68 m
Height	6.4 m
Solar array
Stabilization
DC power
Design lifetime


 DMSP B5D2-3

Also called USA 026 or DMSP 19543

General

Designation	18123 / 87053A
Launch date	20 Jun 1987 at 02:34 UT
Country of origin	United States
Mission	Military: meteorology
Perigee/Apogee	828/848 km
Inclination	98.8°
Period	101.7 min
Launch vehicle	Atlas E59
Launch site	Vandenberg
Mass at launch	822 kg

Must detect tropical cyclones and evaluate the intensity of storms.

Technical data

Specifications


 DMSP B5D2-7

Also called USA 106 and DMSP 5D F12 or DMSP 23545

General

Designation	23233 / 94057A
Launch date	29 Aug 1994 at 17:38 UT
Country of origin	United States
Mission	Military: meteorology
Perigee/Apogee	840/860 km
Inclination	98.9°
Period	101.9 min
Launch vehicle	Atlas E20
Launch site	Vandenberg

It carries instruments to measure energetic particles in the magnetosphere and photometers to scan auroral displays.

Technical data

Specifications


 DMSP B5D2-8

Also called USA 109 and DMSP 5D F13 or DMSP 24547

General

Designation	23533 / 95015A
Launch date	24 Mar 1995 at 14:05 UT
Country of origin	United States
Mission	Military: meteorology
Perigee/Apogee	846/854 km
Inclination	98.8°
Period	101.9 min
Launch vehicle	Atlas E45
Launch site	Vandenberg SLC3

The satellite carries the OLS (Operational Linescan System) weather imager, and a set of microwave sounders and particle detectors.

The launch vehicle was the last Atlas E, a refurbished intercontinental ballistic missile which had been built in the early 1960s.

Technical data

Specifications


 Program: Dong Fang Hong

Means "The Orient is red", also called DFH or PRC

People's Republic of China program which contains numerous sub-programs. Very few details are available on this program.


Program: Dong Fang Hong

Dong Fang Hong 01 Dong Fang Hong 02 Dong Fang Hong 03 Dong Fang Hong 04 Dong Fang Hong 05 Dong Fang Hong 06 Dong Fang Hong 07 Dong Fang Hong 08 Dong Fang Hong 09 Dong Fang Hong 10 Dong Fang Hong 11 Dong Fang Hong 12 Dong Fang Hong 13 Dong Fang Hong 14 Dong Fang Hong 15 Dong Fang Hong 16	Dong Fang Hong 17 Dong Fang Hong 18 Dong Fang Hong 19 Dong Fang Hong 20 Dong Fang Hong 21 Dong Fang Hong 22 Dong Fang Hong 23 Dong Fang Hong 24 Dong Fang Hong 25 Dong Fang Hong 26 Dong Fang Hong 30 Dong Fang Hong 31 Dong Fang Hong 32 Dong Fang Hong 33 Dong Fang Hong 34 Dong Fang Hong 35	Dong Fang Hong 36 Dong Fang Hong 37 Dong Fang Hong 38 Dong Fang Hong 39 Dong Fang Hong 40 Dong Fang Hong 41


Feng Yun 1's payload

VHRR (Very High Resolution Radiometer)

Wavebands	0.58-0.68 µm (visible) 0.725-1.1 µm (near IR) 0.48-0.53 µm (visible) 0.53-0.58 µm (visible) 10.5-12.5 µm (thermal IR)
Resolution	1.1 km (visible) 4 km (IR)
Swath width	3200 km

Equipped with 2 of those radiometers


STTW's specifications

Shiyan Tongbu Tongxin Weixing means experimental synchronous communications satellite. Could also be named DFH 1

Prime contractor	Chinese industry
Platform	STTW
Mass at launch	1024 kg
Mass in orbit	approx. 450 kg
Diameter	2.1 m
Solar array	cells mounted on cylindrical body
Stabilization	Spin stabilized
DC power
Design lifetime	4 years


STTW's C-band

Main transponders	2
Backup transponders
Power	10 W (TWTA)
Bandwidth	36 MHz
Coverage	China
EIRP	32 dBW
Polarization	linear H


DFH 2's specifications

Prime contractor	Chinese industry
Platform	DFH 2
Mass at launch
Mass in orbit
Diameter
Solar array
Stabilization	Spin stabilized
DC power
Design lifetime	4 years?


DFH 2's C-band

Main transponders	4
Backup transponders
Power	10 W (TWTA)
Bandwidth	36 MHz
Coverage	China
EIRP	32 dBW
Polarization	linear H


DFH 3's specifications

Prime contractor	CAST/DASA
Platform	DFH 3
Mass at launch	2230 kg
Mass in orbit	1100 kg
Length
Width
Height
Stabilization	3 axis
DC power
Design lifetime	8 years
Capacity	6 tv channels and 8000 phone calls per minute!


DFH 3's C-band

Main transponders	24
Backup transponders
Power	6 transponders of 20 W (TWTA) 18 transponders of 10 W (TWTA)
Bandwidth	36 MHz
Coverage	China
EIRP	6 transponders: 38 dBW 18 transponders: 35 dBW
Polarization


 Dong Fang Hong 01

Also called Mao 1

General

Designation	04382 / 70034A
Launch date	24 Apr 1970
Country of origin	China
Mission	Scientific
Perigee/Apogee	431/2163 km
Inclination	68.4°
Period	111.5 min
Launch vehicle	Long March 1
Launch site	Jiuquan
Mass at launch	173 kg


 Dong Fang Hong 02

Also called Mao 2

General

Designation	05007 / 71018A
Launch date	3 Mar 1971
Country of origin	China
Mission	Scientific (Shijian)
Perigee/Apogee	265/1833 km
Inclination	69.8°
Period	106.1 min
Launch vehicle
Launch site	Jiuquan


 Dong Fang Hong 03

Also called Mao 3

General

Designation	08053 / 75070A
Launch date	26 Jul 1975
Country of origin	China
Mission	Remote sensing (JSSW)
Perigee/Apogee	190/455 km
Inclination	69°
Period	90.9 min
Launch vehicle
Launch site	Jiuquan
End of life

Decay	14 Sep 1975


 Dong Fang Hong 04

Also called Mao 4 or FSW 0.1

General

Designation	08452 / 75111A
Launch date	26 Nov 1975
Country of origin	China
Mission	Remote sensing (FSW 0)
Perigee/Apogee	173/483 km
Inclination	63°
Period	91.1 min
Launch vehicle	Long March 2C (first flight)
Launch site	Jiuquan
End of life

Out of service	3 Dec 1975
Cause	Normal (photos recovery)
Decay	29 Dec 1975


 Dong Fang Hong 05

Also called Mao 5

General

Designation	08488 / 75119A
Launch date	16 Dec 1975
Country of origin	China
Mission	Remote sensing (JSSW)
Perigee/Apogee	186/387 km
Inclination	69°
Period	90.3 min
Launch vehicle
Launch site	Jiuquan
End of life

Decay	27 Jan 1976


 Dong Fang Hong 06

Also called Mao 6

General

Designation	09394 / 76087A
Launch date	30 Aug 1976
Country of origin	China
Mission	Remote sensing (JSSW)
Perigee/Apogee	195/2145 km
Inclination	69.2°
Period	108.8 min
Launch vehicle
Launch site	Jiuquan
End of life

Decay	25 Nov 1978


 Dong Fang Hong 07

Also called Mao 7 or FSW #?

General

Designation	09587 / 76117A
Launch date	7 Dec 1976
Country of origin	China
Mission	Remote sensing (FSW)
Perigee/Apogee	172/489 km
Inclination	59.4°
Period	91.1 min
Launch vehicle
Launch site	Jiuquan
End of life

Decay	2 Jan 1977


 Dong Fang Hong 08

Also called Mao 8 or FSW #?

General

Designation	10611 / 78011A
Launch date	26 Jan 1978
Country of origin	China
Mission	Remote sensing (FSW)
Perigee/Apogee	186/507 km
Inclination	57°
Period	91.4 min
Launch vehicle
Launch site	Jiuquan
End of life

Decay	7 Feb 1978


 Dong Fang Hong 09

General

Designation	12842 / 81093A
Launch date	19 Sep 1981
Country of origin	China
Mission	Scientific: ionosphere study (Shijian)
Perigee/Apogee	232/1598 km
Inclination	59.5°
Period	103.3 min
Launch vehicle
Launch site	Jiuquan
End of life

Decay	19 Sep 1981


 Dong Fang Hong 10

General

Designation	12843 / 81093B
Launch date	19 Sep 1981
Country of origin	China
Mission	(Shijian)
Perigee/Apogee	233/1615 km
Inclination	59.4°
Period	103.5 min
Launch vehicle
Launch site	Jiuquan
End of life

Decay	6 Oct 1982


 Dong Fang Hong 11

General

Designation	12845 / 81093D
Launch date	19 Sep 1981
Country of origin	China
Mission	(Shijian)
Perigee/Apogee	232/1608 km
Inclination	59.4°
Period	103.4 min
Launch vehicle
Launch site	Jiuquan
End of life

Decay	17 Aug 1982


 Dong Fang Hong 12

Also called FSW #?

General

Designation	13521 / 82090A
Launch date	9 Sep 1982
Country of origin	China
Mission	Remote sensing (FSW)
Perigee/Apogee	172/392 km
Inclination	63°
Period	90.2 min
Launch vehicle
Launch site	Jiuquan
End of life

Decay	21 Sep 1982


 Dong Fang Hong 13

Also called FSW #?

General

Designation	14288 / 83086A
Launch date	19 Aug 1983
Country of origin	China
Mission	Remote sensing (FSW)
Perigee/Apogee	170/493 km
Inclination	63.3°
Period	91.2 min
Launch vehicle
Launch site	Jiuquan
End of life

Decay	3 Sep 1983


 Dong Fang Hong 14

General

Designation	14670 / 84008A
Launch date	29 Jan 1984
Country of origin	China
Mission	(Shijian)
Perigee/Apogee	484/6446 km
Inclination	36.1°
Period	162 min
Launch vehicle	Long March 3
Launch site	Jiuquan


 Dong Fang Hong 15

Also called STTW 0

General

Designation	14899 / 84035A
Launch date	8 Apr 1984
Country of origin	China
Mission	Telecommunications
Geostationary orbit
Launch vehicle
Launch site	Xichang

Maybe a similar satellite was failed at launch earlier in the same year?

End of life

Out of service	yes
Technical data

Specifications

C-band


 Dong Fang Hong 16

Also called FSW #?

General

Designation	15279 / 84098A
Launch date	12 Sep 1984
Country of origin	China
Mission	Remote sensing (FSW)
Perigee/Apogee	172/398 km
Inclination	67.9°
Period	90.2 min
Launch vehicle
Launch site	Jiuquan
End of life

Decay	29 Sep 1984


 Dong Fang Hong 17

Also called FSW #?

General

Designation	16177 / 85096A
Launch date	21 Oct 1985
Country of origin	China
Mission	Remote sensing (FSW)
Perigee/Apogee	171/393 km
Inclination	63°
Period	90.2 min
Launch vehicle
Launch site	Jiuquan
End of life

Decay	7 Nov 1985


 Dong Fang Hong 18

Also called STTW 1

General

Designation	16526 / 86010A
Launch date	1 Feb 1986
Country of origin	China
Mission	Telecommunications
Geostationary orbit	103°E
Launch vehicle
Launch site	Xichang
End of life

Out of service	Apr 1995
Technical data

Specifications

C-band


 Dong Fang Hong 19

Also called FSW #?

General

Designation	17001 / 86076A
Launch date	6 Oct 1986
Country of origin	China
Mission	Remote sensing (FSW)
Perigee/Apogee	169/337 km
Inclination	57°
Period	89.6 min
Launch vehicle
Launch site	Jiuquan
End of life

Decay	23 Oct 1986


 Dong Fang Hong 20

Also called FSW #?

General

Designation	18306 / 87067A
Launch date	5 Aug 1987
Country of origin	China
Mission	Remote sensing (FSW)
Perigee/Apogee	169/366 km
Inclination	63°
Period	89.9 min
Launch vehicle
Launch site	Jiuquan
End of life

Decay	23 Aug 1987


 Dong Fang Hong 21

Also called FSW #?

General

Designation	18341 / 87075A
Launch date	8 Sep 1987
Country of origin	China
Mission	Remote sensing (FSW)
Perigee/Apogee	181/222 km
Inclination	63°
Period	88.5 min
Launch vehicle
Launch site	Jiuquan
End of life

Decay	4 Oct 1987


 Dong Fang Hong 22

Also called STTW 2 or Chinasat 1

General

Designation	18922 / 88014A
Launch date	7 Mar 1988
Country of origin	China
Mission	Telecommunications
Geostationary orbit	87.5°E, inclined
Launch vehicle
Launch site	Xichang
Technical data

Specifications

C-band


 Dong Fang Hong 23

Also called FSW #?

General

Designation	19368 / 88067A
Launch date	5 Aug 1988
Country of origin	China
Mission	Remote sensing (FSW)
Perigee/Apogee	204/311 km
Inclination	63°
Period	89.7 min
Launch vehicle
Launch site	Jiuquan
End of life

Decay	13 Aug 1988


 Dong Fang Hong 24

Also called Feng Yun 1-1, means "wind and cloud"

General

Designation	19467 / 88080A
Launch date	6 Sep 1988 at 20:30 UT
Country of origin	China
Mission	Meteorology
Perigee/Apogee	832/937 km
Inclination	99.2°
Period	102.7 min
Launch vehicle	Long March 4
Launch site	Taiyuan

Mission: weather forcasting and environment monitoring; cloud, ice, snow and flood monitoring; sea color and surface temperature.

End of life

Cause	Failed after 39 days
Technical data

Payload

Specifications

Prime contractor	State Met Administration
Mass at launch	750 kg
Stabilization	3 axis
Design lifetime	6 months

Transmits on 137.8 MHz.


 Dong Fang Hong 25

Also called STTW 3 or Chinasat 2

General

Designation	19710 / 88111A
Launch date	22 Dec 1988
Country of origin	China
Mission	Telecommunications
Geostationary orbit	110.5°E, inclined
Launch vehicle
Launch site	Xichang
Technical data

Specifications

C-band


 Dong Fang Hong 26

Also called STTW 4 or Chinasat 3

General

Designation	20473 / 90011A
Launch date	4 Feb 1990
Country of origin	China
Mission	Telecommunications
Geostationary orbit	98°E, inclined
Launch vehicle
Launch site	Xichang
Technical data

Specifications

C-band


 Dong Fang Hong 30

Also called Feng Yun 1-2, means "wind and cloud"

General

Designation	20788 / 90081A
Launch date	3 Sep 1990
Country of origin	China
Mission	Meteorology
Perigee/Apogee	875/897 km
Inclination	98.8°
Period	102.7 min
Launch vehicle	Long March 3
Launch site	Taiyuan

Mission: weather forcasting and environment monitoring; cloud, ice, snow and flood monitoring; sea color and surface temperature.

Technical data

Payload

Specifications

Prime contractor	State Met Administration
Mass at launch	750 kg
Stabilization	3 axis
Design lifetime	1 year

APT-Downlink is approximately 36kHz wide FM-modulated, APT-FAX format.

APT downlink freq.	137.800MHz (currently not active)
HRPT downlink freq.	? (around 1700MHz?, active)
Beacon freq.	?


 Dong Fang Hong 31

Also called Atmosphere 1

General

Designation	20789 / 90081B
Launch date	3 Sep 1990
Country of origin	China
Mission
Perigee/Apogee	789/811 km
Inclination	99°
Period	100.9 min
Launch vehicle
Launch site	Taiyuan
End of life

Decay	11 Mar 1991


 Dong Fang Hong 32

Also called Atmosphere 2

General

Designation	20790 / 90081C
Launch date	3 Sep 1990
Country of origin	China
Mission
Perigee/Apogee	596/629 km
Inclination	99°
Period	97 min
Launch vehicle
Launch site	Taiyuan
End of life

Decay	24 Jul 1991


 Dong Fang Hong 33

Also called FSW #?

General

Designation	20838 / 90089A
Launch date	5 Oct 1990
Country of origin	China
Mission	Remote sensing (FSW)
Perigee/Apogee	209/312 km
Inclination	57°
Period	89.7 min
Launch vehicle
Launch site	Juiquan
End of life

Decay	23 Oct 1990


 Dong Fang Hong 34

Also called STTW 5 or Chinasat 4

General

Designation	21833 / 91088A
Launch date	28 Dec 1991
Country of origin	China
Mission	Telecommunications
Perigee/Apogee	2017/34047 km
Inclination	31.5°
Period	632.6 min
Launch vehicle
Launch site
End of life

Out of service	28 Dec 1991
Cause	Did not reach GEO
Technical data

Specifications

C-band


 Dong Fang Hong 35

Also called FSW 2.#?

General

Designation	22072 / 92051A
Launch date	9 Aug 1992
Country of origin	China
Mission	Remote sensing (FSW 2)
Perigee/Apogee	171/332 km
Inclination	63.1°
Period	89.5 min
Launch vehicle	Long March 2D (first launch)
Launch site	Juiquan
End of life

Decay	1 Sep 1992


 Dong Fang Hong 36

Also called FSW 2.#?

General

Designation	22162 / 92064B
Launch date	6 Oct 1992
Country of origin	China
Mission	Remote sensing (FSW 2)
Perigee/Apogee	213/309 km
Inclination	63°
Period	89.7 min
Launch vehicle	Long March 2D
Launch site	Jiuquan
End of life

Decay	31 Oct 1992


 Dong Fang Hong 37

Also called Jianbing 93 or FSW 1.#?

General

Designation	22859 / 93063A (or 22870 / 93063H)
Launch date	8 Oct 1993 at 08:00 UT
Country of origin	China
Mission	Remote sensing (FSW 1)
Perigee/Apogee	177/2629 km
Inclination	56.5°
Period	113.9 min
Launch vehicle	Long March 2C
Launch site	Jiuquan

Contained a Mao's medallion of 28 g made of 44 South-African diamants that should have been sold by auction at its return on earth by Zhonyu company.

The reentry vehicle fired its deorbit motor successfully but, alas, in the wrong direction; the capsule ended up in a 187 x 3016 km orbit, starting from a low 196 x 251 km orbit.

End of life

Decay	12 Mar 1996


 Dong Fang Hong 38

Also called Shijian 4 or SJ 4. Means "Practice 4"

General

Designation	22996 / 94010A
Launch date	8 Feb 1994
Country of origin	China
Mission	Scientific & Technology
Perigee/Apogee	221/34459 km
Inclination	28.41°
Period	605.89 min
Launch vehicle	Long March 3A
Launch site	Xichang

It carried six instruments for measuring particle fluxes and spacecraft electric potential.

First launch for LM 3A


 Dong Fang Hong 39

Also called Shijian 4-2 or SJ 4-2. Means "Practice 4-2"

General

Designation	23009 / 94010B
Launch date	8 Feb 1994
Country of origin	China
Mission	Simulated satellite
Perigee/Apogee	211/32578 km
Inclination	27.49°
Period	570.03 min
Launch vehicle	Long March 3A
Launch site	Xichang

Mockup of the new DFH 3 telecommunication series (see Dong Fang Hong 41)


 Dong Fang Hong 40

Also called FSW 2.#?, Fanhui Shi Weixing

General

Designation	23145 / 94037A
Launch date	3 Jul 1994 at 08:00 UT
Country of origin	China
Mission	Remote sensing (FSW 2)
Perigee/Apogee	176/355 km
Inclination	62.9°
Period	89.6 min
Launch vehicle	Long March 2D
Launch site	Jiuquan
End of life

Decay	payload: 15 Jul 1994 service module: 13 Sep 1994


 Dong Fang Hong 41

General

Designation	23415 / 94080A
Launch date	29 Nov 1994 at 17:02 UT
Country of origin	China
Mission	Telecommunications
Geostationary orbit	should have been in 125°E slot
Launch vehicle	Long March 3A
Launch site	Xichang

First satellite of the DFH 3 generation, built with a 20% German participation (Daimler Benz Aerospace/MBB)

End of life

Out of service	9 Jan 1995
Cause	fuel leak
Technical data

Specifications

C-band


 Dong Fang Hong 42

Also called Chinasat 6

General

Designation
Launch date	planned in early 1996
Country of origin	China
Mission	Telecommunications
Geostationary orbit	125°E ?
Launch vehicle	Long March
Launch site	Xichang

To replace Dong Fang Hong 41

Technical data

Has a 8-year lifetime and 24 C-band transponders. It might be this kind of bird:

Specifications

C-band


 Dove

Short for Digital Orbiting Voice Encoder. Also called Microsat 2 or DO-17 or Oscar 17

General

Designation	20440 / 90005E
Launch date	22 Jan 1990
Country of origin	Brazil
Mission	Telecommunications
Perigee/Apogee	781/797 km
Inclination	98.6°
Period	100.6 min
Launch vehicle	Ariane V35
Mass at launch	9 kg

Based on a Amsat-NA Microsat bus

Technical data

Downlink	1200 bps Bell 202 AX.25, same as used in terrestrial Packet Radio, Synthesized Voice Beacon.
	145.825, 145.825 MHz
S-Band beacon	2401.221 MHz

Passive magnetic stabilization


 Program: DSCS

Defense Satellite Communication System, also called USGCSS

American geostationary satellite program. Designed to provide military telecommunications. Operated by the US Space Command

First generation

See IDSCP

Second generation

Satellites were launched by pairs to GEO

Third generation

Specifications

USAF asked LM [in mid-1995] for a cost estimate on upgrades to the remaining ground-spare DSCS-3s to extend their lives somewhat: improved thrusters, better solar cells, more efficient amplifiers in the high-power channels. The DSCS-3 production line shut down several years ago, and the USAF wants to postpone the start of development on DSCS-4.


Program: DSCS

DSCS 2-01	DSCS 2-02	DSCS 2-03	DSCS 2-04
DSCS 2-05	DSCS 2-06	DSCS 2-07	DSCS 2-08
DSCS 2-11	DSCS 2-12	DSCS 2-13	DSCS 2-14
DSCS 2-15	DSCS 2-16
DSCS 3-01	DSCS 3-02	DSCS 3-03	DSCS 3-04
DSCS 3-05	DSCS 3-06	DSCS 3-07	DSCS 3-08
DSCS 3-09


DSCS 3's specifications

Prime contractor	Lockheed martin (part that used to be General Electric)
Platform
Mass at launch	2 tons or 1170 kg ?
Mass in orbit
Length	2 m
Width	2.7 m
Height
Stabilization
DC power
Design lifetime

Equipped for S-, X- and SHF-band (6 transponders) downlink. Fleet composed of 14 satellites


 DSCS 2-01

General

Designation	05587 / 71095A
Launch date	3 Nov 1971
Country of origin	United States
Mission	Military: Telecommunications
Geostationary orbit	see below
Launch vehicle
Launch site	Cape Canaveral
End of life

Out of service	yes


 DSCS 2-02

General

Designation	05588 / 71095B
Launch date	3 Nov 1971
Country of origin	United States
Mission	Military: Telecommunications
Geostationary orbit
Launch vehicle
Launch site	Cape Canaveral
End of life

Out of service	yes


 DSCS 2-03

General

Designation	06973 / 73100A
Launch date	13 Dec 1973
Country of origin	United States
Mission	Military: Telecommunications
Geostationary orbit
Launch vehicle
Launch site	Cape Canaveral
End of life

Out of service	yes


 DSCS 2-04

General

Designation	06974 / 73100B
Launch date	13 Dec 1973
Country of origin	United States
Mission	Military: Telecommunications
Geostationary orbit
Launch vehicle
Launch site	Cape Canaveral
End of life

Out of service	yes


 DSCS 2-05

General

Designation	07807 / 75040A
Launch date	20 May 1975
Country of origin	United States
Mission	Military: Telecommunications
Geostationary orbit
Launch vehicle
Launch site	Cape Canaveral
End of life

Out of service	20 May 1975
Cause	Launch failure
Decay	26 May 1975


 DSCS 2-06

General

Designation	07808 / 75040B
Launch date	20 May 1975
Country of origin	United States
Mission	Military: Telecommunications
Geostationary orbit
Launch vehicle
Launch site	Cape Canaveral
End of life

Out of service	20 May 1975
Cause	Launch failure
Decay	26 May 1975


 DSCS 2-07

General

Designation	10000 / 77034A
Launch date	12 May 1977
Country of origin	United States
Mission	Military: Telecommunications
Geostationary orbit
Launch vehicle
Launch site	Cape Canaveral
End of life

Out of service	yes


 DSCS 2-08

General

Designation	10001 / 77034B
Launch date	12 May 1977
Country of origin	United States
Mission	Military: Telecommunications
Geostationary orbit
Launch vehicle
Launch site	Cape Canaveral
End of life

Out of service	yes


 DSCS 2-11

General

Designation	11144 / 78113A
Launch date	14 Dec 1978
Country of origin	United States
Mission	Military: Telecommunications
Geostationary orbit
Launch vehicle
Launch site	Cape Canaveral
End of life

Out of service	yes


 DSCS 2-12

General

Designation	11145 / 78113B
Launch date	14 Dec 1978
Country of origin	United States
Mission	Military: Telecommunications
Geostationary orbit
Launch vehicle
Launch site	Cape Canaveral
End of life

Out of service	yes


 DSCS 2-13

Also called OPS 9443

General

Designation	11621 / 79098A
Launch date	21 Nov 1979
Country of origin	United States
Mission	Military: Telecommunications
Geostationary orbit
Launch vehicle
Launch site	Cape Canaveral
End of life

Out of service	yes


 DSCS 2-14

Also called OPS 9444

General

Designation	11622 / 79098B
Launch date	21 Nov 1979
Country of origin	United States
Mission	Military: Telecommunications
Geostationary orbit	see below
Launch vehicle
Launch site	Cape Canaveral
End of life

Out of service	yes
Technical data

Downlinks in X-band


 DSCS 2-15

General

Designation	13636 / 82106A
Launch date	30 Oct 1982
Country of origin	United States
Mission	Military: Telecommunications
Geostationary orbit	see below
Launch vehicle	Titan 34D
Launch site	Cape Canaveral
Location

Begin	End	Position
L: 30 Oct 1982		?
Mar 1995		65°E, inclined
Technical data

Downlinks in X-band


 DSCS 2-16

Also called USA 043

General

Designation	20202 / 89069A
Launch date	4 Sep 1989
Country of origin	United States
Mission	Military: Telecommunications
Geostationary orbit	n/a
Launch vehicle	Titan 34D
Launch site	Cape Canaveral
Technical data

Downlinks in X-band


 DSCS 3-01

General

Designation	13637 / 82106B
Launch date	30 Oct 1982
Country of origin	United States
Mission	Military: Telecommunications
Geostationary orbit	see below
Launch vehicle	Titan 34D + IUS
Launch site	Cape Canaveral
Location

Begin	End	Position
L: 30 Oct 1982		?
Mar 1995		130°W, inclined
Technical data

Specifications


 DSCS 3-02

Also called USA 011

General

Designation	16116 / 85092B
Launch date	3 Oct 1985
Country of origin	United States
Mission	Military: Telecommunications
Geostationary orbit	see below
Launch vehicle	STS 28 + IUS
Launch site	Cape Canaveral
Location

Begin	End	Position
L: 3 Oct 1985		?
Mar 1995	?	60°E
Technical data

Specifications

Downlinks in P- (250 MHz), S-, C- and X-band


 DSCS 3-03

Also called USA 012

General

Designation	16117 / 85092C
Launch date	3 Oct 1985
Country of origin	United States
Mission	Military: Telecommunications
Geostationary orbit	n/a
Launch vehicle	STS 28 + IUS
Launch site	Cape Canaveral
Location

Begin	End	Position
L: 3 Oct 1985		?
Mar 1995	?	45°W
Technical data

Specifications

Downlinks in P- (250 MHz), S-, C- and X-band


 DSCS 3-04

Also called USA 044

General

Designation	20203 / 89069B
Launch date	4 Sep 1989
Country of origin	United States
Mission	Military: Telecommunications
Geostationary orbit	n/a
Launch vehicle	Titan 34D + transtage
Launch site	Cape Canaveral
Location

Begin	End	Position
L: 4 Sep 1989		?
Mar 1995	?	52.5°W
Technical data

Specifications

Downlinks in P- (250 MHz), S-, C- and X-band


 DSCS 3-05

Also called USA 078

General

Designation	21873 / 92006A
Launch date	11 Feb 1992
Country of origin	United States
Mission	Military: Telecommunications
Geostationary orbit	n/a
Launch vehicle	Atlas Centaur + IABS

First satellite of the 3B generation. This generation is equipped with reinforced plating to resist to the explosion of an atomic bomb.

Technical data

Specifications


 DSCS 3-06

Also called USA 082

General

Designation	22009 / 92037A
Launch date	2 Jul 1992
Country of origin	United States
Mission	Military: Telecommunications
Geostationary orbit	see below
Launch vehicle	Atlas Centaur + IABS
Location

Begin	End	Position
L: 31 Jan 1984		?
Mar 1995	?	12°W
Technical data

Specifications

Downlinks in P- (250 MHz), S-, C- and X-band


 DSCS 3-07

Also called USA 093

General

Designation	22719 / 93046A
Launch date	19 Jul 1993
Country of origin	United States
Mission	Military: Telecommunications
Geostationary orbit	n/a
Launch vehicle	Atlas Centaur + IABS
Technical data

Specifications


 DSCS 3-08

Also called USA 097

General

Designation	22913 / 93074A
Launch date	28 Nov 1993
Country of origin	United States
Mission	Military: Telecommunications
Geostationary orbit	n/a
Launch vehicle	Atlas Centaur + IABS
End of life

Out of service	28 Nov 1993
Cause	didn't reach GEO, failure of the IABS?
Technical data

Specifications


 DSCS 3-09

Also called USA 113

General

Designation	23628 / 95038A
Launch date	31 Jul 1995
Country of origin	United States
Mission	Military: Telecommunications
Geostationary orbit	n/a
Launch vehicle	Atlas Centaur + IABS
Technical data

Specifications


 Program: DSP

Defense Support Program

Military geostationary satellite program for early warning and detection of nuclear explosions.

The first generation of those satellites was IMEWS.


Program: DSP

DSP F12

DSP F13

DSP F14

DSP F15

DSP 3-4

DSP 3-5


 DSP F12

Also called USA 007

General

Designation	15453 / 84129A
Launch date	22 Dec 1984
Country of origin	United States
Mission	Military: early warning
Geostationary orbit	n/a
Launch vehicle
Launch site	Cape Canaveral


 DSP F13

Also called USA 028

General

Designation	18583 / 87097A
Launch date	29 Nov 1987
Country of origin	United States
Mission	Military: early warning
Geostationary orbit	n/a
Launch vehicle
Launch site	Cape Canaveral


 DSP F14

Also called USA 039

General

Designation	20066 / 89046A
Launch date	14 Jun 1989
Country of origin	United States
Mission	Military: early warning
Geostationary orbit	n/a
Launch vehicle	Titan 4
Launch site	Cape Canaveral


 DSP F15

Also called USA 065

General

Designation	20929 / 90095A
Launch date	13 Nov 1990
Country of origin	United States
Mission	Military: early warning
Geostationary orbit	n/a
Launch vehicle	Titan 4


 DSP 3-4

Also called USA 075 or DSP F16

General

Designation	21805 / 91080B
Launch date	24 Nov 1991
Country of origin	United States
Mission	Military: early warning
Geostationary orbit	n/a
Launch vehicle	STS 44
Mass at launch	2350 kg

Cost: $275 million


 DSP 3-5

Also called USA 107 or DSP F17

General

Designation	23435 / 94084A
Launch date	22 Dec 1994 at 22:19 UT
Country of origin	United States
Mission	Military: early warning
Geostationary orbit	n/a
Launch vehicle	Titan 4

Built by TRW, wide field infrared telescope to provide real-time warning of missile launches


 Dynamics Explorer 1

Also called DE A

General

Designation	12624 / 81070A
Launch date	3 Aug 1981
Country of origin	United States
Mission	Scientific: magnetosphere study
Perigee/Apogee	468/23322 km
Inclination	88.8°
Period	409.7 min
Launch vehicle	Thor Delta #155


 Dynamics Explorer 2

Also called DE B

General

Designation	12625 / 81070B
Launch date	3 Aug 1981
Country of origin	United States
Mission	Scientific: magnetosphere and ionosphere study
Perigee/Apogee	304/1002 km
Inclination	90°
Period	97.8 min
Launch vehicle	Thor Delta #155
End of life

Decay	19 Feb 1983


 Program: Echo

American experimental telecommunication program


Program: Echo

Echo 1

Echo 2


 Echo 1

Also called Echo 1A because the first Echo had a launch failure

General

Designation	00049 / 60009A
Launch date	12 Aug 1960
Country of origin	United States
Mission	Telecommunications and geodesy
Perigee/Apogee	966/2157 km
Inclination	47.3°
Period	117.3 min
Launch vehicle	Thor Delta #2
Mass at launch	61 kg

Plastic 30.5 m ball covered of mylar aluminumed that reflected radioelectric signals.

It enabled the first satellite telephone link and the broadcast of a TV program from California to Massachussets on 24 Feb 1962.

End of life

Decay	24 May 1968


 Echo 2

General

Designation	00740 / 64004A
Launch date	25 Jan 1964
Country of origin	United States
Mission	Telecommunications and geodesy
Perigee/Apogee	1030/1315 km
Inclination	81.5°
Period	108.8 min
Launch vehicle	Thor Agena
Launch site	Vandenberg
Mass at launch	256 kg

Plastic 41 m ball covered 2 aluminum sheets with a mylar sheet in between.

End of life

Decay	7 Sep 1969


 Program: Echostar

American DBS program operated by EchoStar Satellite Corp. The system will power the DISH system (Digital Sky Highway) Total Echostar project: $335 million

The FCC granted EchoStar Satellite Corp. an extension of its satellite construction permit, and granted EchoStar subsidiary DirectSat an extension until Aug. 15, 1999, for construction and launch of its satellites to be located at 119 degrees and 175 degrees west longitude.

In late Dec 1995, EchoStar agreed to purchase Direct Broadcasting Satellite Corp., a privately held company, for about $7.8 million. In November 1994, EchoStar purchased about 40 percent of DBSC.

In January 1996: Pending final FCC approvals and other conditions, Echostar controls frequency allocations at 61.5, 119, 148 and 175 degrees west longitude (90 transponders of DBS spectrum)

Contact

Echostar

90 Inverness Circle East, Englewood, CO 80112, USA

Tel: +1-303-799-8222

Fax: +1-303-799-3632


Program: Echostar

Echostar 1

Echostar 2

Echostar 3

Echostar 4


 Echostar 1

General

Designation	23754 / 95073A
Launch date	28 Dec 1995 at 11:50 UT
Country of origin	United States
Mission	Telecommunications
Geostationary orbit	119°W
Launch vehicle	Long March 2E
Launch site	Xichang
Technical data

Specifications

Prime contractor	Lockheed Martin Astro Space
Platform	GE 7000
Mass at launch
Mass in orbit
Dimension	4.08 x 2.22 x 2.54 m?
Solar array	24.5 m span?
Stabilization	3 axis
DC power	BOL: 6400 W? EOL: 5000 W?
Design lifetime	12 or 15 years
Ku-band

Main transponders	16
Backup transponders
Power	130 W
Bandwidth	24 MHz
Coverage	CONUS
EIRP
Polarization


 Echostar 2

General

Designation
Launch date	planned in the 3rd quarter of 1996
Country of origin	United States
Mission	Telecommunications
Geostationary orbit	co-located
Launch vehicle	Ariane 4
Launch site

Launch opportunities had been reserved with Long March and Proton but finally after the numerous launch problems, Echostar choose Ariane for launch.

The launch by Proton required to develop a new adapter, which has been called by the weight Echostar 2 (2041 kg) which does not permit the use of the former.

Built by GE Astro


 Echostar 3

planned between September and November 1997

a Proton and a Long March 3B have been booked


 Echostar 4

to be launched by Proton


 Program: Ekran

Soviet direct TV program


Program: Ekran

Ekran 01	Ekran 02	Ekran 03	Ekran 04
Ekran 05	Ekran 06	Ekran 07	Ekran 08
Ekran 09	Ekran 10	Ekran 11	Ekran 12
Ekran 13	Ekran 14	Ekran 15	Ekran 16
Ekran 17	Ekran 18	Ekran 19	Ekran 20


 Ekran's specifications

Prime contractor	NPO Prikadnoy Mekaniki (PM)
Platform	Ekran
Mass at launch	1970 kg
Diameter	2 m
Height	5 m
Stabilization	3 axis
Design lifetime	3 years
UHF-band

Main transponders	1
Backup transponders	1
Power	200 W
Bandwidth	24 MHz
Coverage	CIS and part of Asia
EIRP	55.5 dBW
Frequencies	Uplink: C-band (6 GHz) Downlink: 714 MHz


 Ekran 01

General

Designation	09503 / 76107A
Launch date	26 Oct 1976
Country of origin	CIS
Mission	Telecommunications
Geostationary orbit	99°E
Launch vehicle	Proton #60
End of life

Out of service	yes
Technical data

Specifications


 Ekran 02

General

Designation	10365 / 77092A
Launch date	20 Sep 1977
Country of origin	CIS
Mission	Telecommunications
Geostationary orbit
Launch vehicle	Proton #65
End of life

Out of service	yes
Technical data

Specifications


 Ekran 03

General

Designation	11273 / 79015A
Launch date	21 Feb 1979
Country of origin	CIS
Mission	Telecommunications
Geostationary orbit
Launch vehicle	Proton #76
End of life

Out of service	yes
Technical data

Specifications


 Ekran 04

General

Designation	11561 / 79087A
Launch date	3 Oct 1979
Country of origin	CIS
Mission	Telecommunications
Geostationary orbit
Launch vehicle	Proton #80
End of life

Out of service	yes
Technical data

Specifications


 Ekran 05

General

Designation	11890 / 80060A
Launch date	14 Jul 1980
Country of origin	CIS
Mission	Telecommunications
Geostationary orbit
Launch vehicle	Proton #84
End of life

Out of service	yes
Technical data

Specifications


 Ekran 06

General

Designation	12120 / 80104A
Launch date	26 Dec 1980
Country of origin	CIS
Mission	Telecommunications
Geostationary orbit
Launch vehicle	Proton #86
End of life

Out of service	yes
Technical data

Specifications


 Ekran 07

General

Designation	12564 / 81061A
Launch date	25 Jun 1981
Country of origin	CIS
Mission	Telecommunications
Geostationary orbit
Launch vehicle	Proton #89
End of life

Out of service	yes
Technical data

Specifications


 Ekran 08

General

Designation	13056 / 82009A
Launch date	5 Feb 1982
Country of origin	CIS
Mission	Telecommunications
Geostationary orbit	99°E
Launch vehicle	Proton #94
End of life

Out of service	yes
Technical data

Specifications


 Ekran 09

General

Designation	13554 / 82093A
Launch date	16 Sep 1982
Country of origin	CIS
Mission	Telecommunications
Geostationary orbit	99°E
Launch vehicle	Proton #99
End of life

Out of service	yes
Technical data

Specifications


 Ekran 10

General

Designation	13878 / 83016A
Launch date	12 Mar 1983
Country of origin	CIS
Mission	Telecommunications
Geostationary orbit
Launch vehicle	Proton #105
End of life

Out of service	yes
Technical data

Specifications


 Ekran 11

General

Designation	14377 / 83100A
Launch date	30 Sep 1983
Country of origin	CIS
Mission	Telecommunications
Geostationary orbit	99°E
Launch vehicle	Proton #113
End of life

Out of service	yes
Technical data

Specifications


 Ekran 12

General

Designation	14821 / 84028A
Launch date	16 Mar 1984
Country of origin	CIS
Mission	Telecommunications
Geostationary orbit	99°E
Launch vehicle	Proton #118
End of life

Out of service	yes
Technical data

Specifications


 Ekran 13

General

Designation	15219 / 84090A
Launch date	24 Aug 1984
Country of origin	CIS
Mission	Telecommunications
Geostationary orbit	99°E
Launch vehicle	Proton #124
End of life

Out of service	yes
Technical data

Specifications


 Ekran 14

General

Designation	15626 / 85024A
Launch date	22 Mar 1985
Country of origin	CIS
Mission	Telecommunications
Geostationary orbit	99°E
Launch vehicle	Proton #131
End of life

Out of service	yes
Technical data

Specifications


 Ekran 15

General

Designation	16729 / 86038A
Launch date	24 May 1986
Country of origin	CIS
Mission	Telecommunications
Geostationary orbit	99°E
Launch vehicle	Proton #142
End of life

Out of service	yes
Technical data

Specifications


 Ekran 16

General

Designation	18328 / 87073A
Launch date	4 Sep 1987
Country of origin	CIS
Mission	Telecommunications
Geostationary orbit	99°E
Launch vehicle	Proton #154
End of life

Out of service	yes
Technical data

Specifications


 Ekran 17

General

Designation	18715 / 87109A
Launch date	27 Dec 1987
Country of origin	CIS
Mission	Telecommunications
Geostationary orbit	99°E
Launch vehicle	Proton #160
End of life

Out of service	yes
Technical data

Specifications


 Ekran 18

General

Designation	19090 / 88036A
Launch date	6 May 1988
Country of origin	CIS
Mission	Telecommunications
Geostationary orbit	99°E
Launch vehicle	Proton #165
End of life

Out of service	yes
Technical data

Specifications


 Ekran 19

General

Designation	19683 / 88108A
Launch date	8 Dec 1988
Country of origin	CIS
Mission	Telecommunications
Geostationary orbit	99°E, inclined
Launch vehicle	Proton #173
Technical data

Specifications


 Ekran 20

General

Designation	22210 / 92074A
Launch date	30 Oct 1992
Country of origin	CIS
Mission	Telecommunications
Geostationary orbit	99°E, inclined
Launch vehicle	Proton #210
Technical data

Specifications


 Electro 1

General

Designation	23327 / 94069A
Launch date	31 Oct 1994
Country of origin	CIS
Mission	Meteorology
Geostationary orbit	76.5°E
Launch vehicle	Proton #228

It will provide cloud cover and sea temperature maps, along with the data on the upper boundaries of clouds and wind speeds, to enable hurricane, floods, and typhoon warnings.

Technical data

Specifications

Prime contractor	VNII-EM
Platform	Electro
Mass at launch
Mass in orbit
Length
Width
Height
Stabilization
DC power
Design lifetime	3 years

L-band (1.6 GHz) capable


 Program: Elekon

LEO system project from the Russian NPO-PM firm with Elbe Space & Technology and KG. Elekon. The system would be carried by 7 modules on Kosmos satellites.

Would be on polar orbits (1150 km apogee). Communications with mobiles: 1.6 GHz (uplink) and 2.5 GHz (downlink). Controling would be in C-band.


 Program: Elektron

Soviet scientific program: Earth's magnetic field, solar radioelectric emissions and Van Allen belts.


Program: Elektron

Elektron 1

Elektron 2

Elektron 3

Elektron 4


 Elektron 1

General

Designation	00746 / 64006A
Launch date	30 Jan 1964
Country of origin	CIS
Mission	Scientific: magnetophere and ionosphere study
Perigee/Apogee	404/6577 km
Inclination	60.8°
Period	162.6 min
Launch vehicle
Launch site	Tyuratam


 Elektron 2

General

Designation	00748 / 64006B
Launch date	30 Jan 1964
Country of origin	CIS
Mission	Scientific: magnetophere study
Perigee/Apogee	5082/63341 km
Inclination	59.9°
Period	1356.4 min
Launch vehicle
Launch site	Tyuratam


 Elektron 3

General

Designation	00829 / 64038A
Launch date	10 Jul 1964
Country of origin	CIS
Mission	Scientific: magnetophere and ionosphere study
Perigee/Apogee	405/6441 km
Inclination	60.8°
Period	161 min
Launch vehicle
Launch site	Tyuratam


 Elektron 4

General

Designation	00830 / 64038B
Launch date	10 Jul 1964
Country of origin	CIS
Mission	Scientific: magnetophere study
Perigee/Apogee	447/66269 km
Inclination	60.8°
Period	1313.8 min
Launch vehicle
Launch site	Tyuratam
End of life

Decay	10 Jul 1964


 Program: Ellipsat

Mobile satellite phone project

Overview

	project 1	project 2
Orbit type	HEO	MEO
Orbit range	Ellipse, 7846 x 520 km	8040 km
Nb of satellites	10	6
Nb of planes	2	1
Inclination	116.5°	0°
Nb beams per satellite	61	61
Coverage	11980 km²	11980 km²
Modulation	CDMA	CDMA
Mobile uplink freq.	S-Band: 2483.5 - 2500 MHz	S-Band: 2483 - 2500 MHz
Satellite mass	650 kg	650 kg
Coverage	Worldwide except South pole	Worldwide except South pole
Operational date	1998 (planned)	1998 (planned)


 Eole

General

Designation	05435 / 71071A
Launch date	16 Aug 1971
Country of origin	France
Mission	Scientific: high atmosphere study
Perigee/Apogee	651/835 km
Inclination	50.2°
Period	99.7 min
Launch vehicle	Scout #75
Mass at launch	80 kg

Meteorological experimental satellite aimed to study wind in the southern hemisphere. Eole destroyed 89 out of 479 balloons it interrogated cause of a human error. When all balloons had disappeared it was used to study oceans currents, iceberg movements, etc.

End of life

Out of service	July 1974


Eorsat
 Program: Eorsat

Electronic Ocean Reconnaissance Satellite

Russian program part of the Cosmos constellation. Those satellites are observation satellites designed to monitor activity of foreign navies.

The series started in 1974 and around 40 satellites had been launched in mid-1995.

Active satellites

Cosmos 2326

Cosmos 2313

Cosmos 2293

Cosmos 2264

Cosmos 2258 (decayed)

Cosmos 2244

Cosmos 2238 (replaced Cosmos 2122)

Former satellites

Cosmos 2122 (decayed)

Cosmos 2107

Cosmos 2103

Cosmos 2096

Cosmos 2060

Cosmos 2046

Technical data

Specifications

Prime contractor	NPO Machinostroenie
Platform
Mass at launch
Mass in orbit
Length
Width
Height
Perigee/Apogee	400 km
Inclination	65°
Period	92 min
Stabilization
DC power
Design lifetime	1.5 years

It uses a low thrust engine to maintain its orbit.


 Program: EOS

Earth Observing System

NASA scientific program part of its Mission to Planet Earth program. It is to be the first integrated satellite and research system designed to observe the linkages among all the components of the Earth system.

Satellite part of the program: Landsat 7, AM-1, PM-1, Chemistry-1, TRMM


Program: EOS

EOS AM

EOS PM-1

EOS Chemistry 1


 EOS AM

General

Designation
Launch date	planned in 1998
Country of origin	United States
Mission	Scientific
Perigee/Apogee
Inclination
Period
Launch vehicle
Launch site
Technical data

Specifications

Prime contractor	Lockheed Martin
Platform
Mass at launch
Mass in orbit
Dimension
Solar array
Stabilization
DC power
Design lifetime

Operates at 2, 13 and 15 GHz


 EOS PM-1

General

Designation
Launch date	planned in 2000
Country of origin	United States
Mission	Scientific
Perigee/Apogee
Inclination
Period
Launch vehicle
Launch site

Contracted together with EOS Chemistry 1 for $398 million; an option on two more crafts could amount the total to $668 million

Technical data

Specifications

Prime contractor	TRW
Platform	AM1200 EOS commun spacecraft bus
Mass at launch
Mass in orbit
Dimension
Solar array
Stabilization
DC power
Design lifetime


 EOS Chemistry 1

General

Designation
Launch date	planned in 2002
Country of origin	United States
Mission	Scientific
Perigee/Apogee
Inclination
Period
Launch vehicle
Launch site

Contracted together with EOS PM-1 for $398 million; an option on two more crafts could amount the total to $668 million

Technical data

Specifications

Prime contractor	TRW
Platform	AM1200 EOS commun spacecraft bus
Mass at launch
Mass in orbit
Dimension
Solar array
Stabilization
DC power
Design lifetime


 ERBS

Earth Radiation Budget Satellite

General

Designation	15354 / 84108B
Launch date	5 Oct 1984
Country of origin	United States
Mission	Scientific: high atmosphere study
Perigee/Apogee	582/593 km
Inclination	57°
Period	96.4 min
Launch vehicle	STS 17
Mass at launch	147 kg

Part of a NASA Earth Radiation Budget Experiment (ERBE) to measure radiation emitted by the Earth and the effect of a solar radiation incident on the Earth.

Technical data

Specifications

Prime contractor	Ball
Mass at launch	2300 kg
Length	1.6 m
Height	3.8 m
Solar array	7 m span
Stabilization	3 axis

Payload: 2 radiometers and SAGE 2 (Stratospheric Aerosol and Gas Experiment) to monitor vertical distribution of aerosols, ozone and carbone dioxide in the stratosphere.


ERS
 Program: ERS

European Remote Sensing satellite

European remote sensing program designed to provide images of the Earth in the microwave spectrum. Primary objectives of the multi-mission payload are in oceanographic science: ocean current patterns, wind velocity, ice coverage, etc. The radar payload allows observations through cloud and darkness.


Program: ERS

ERS 1

ERS 2


 ERS 1

General

Designation	21574 / 91050A
Launch date	17 Jul 1991
Country of origin	Europe
Mission	Remote sensing
Perigee/Apogee	768/769 km
Inclination	98.5°
Period	100.2 min
Orbital cycle	3, 35 and 176 days
Launch vehicle	Ariane V44

ESA's first remote sensing satellite. Cost: $500 million

Since early 1994 the satellite transmits with the backup travelling wave tube because the primary one failed.

Technical data

Specifications

Prime contractor	Dornier
Platform	MMS Spot
Mass at launch	2400 kg
Payload mass	1100 kg
Dry mass	2080 kg
Length	11.8 m
Solar array	11.7 x 2.4 m
SAR antenna	10 x 1 m
Radar altimeter	1.2 m (diameter)
Stabilization	3 axis
DC power	2500 W
Design lifetime	3 years
AMI (Active Microwave Instrument)

Frequency	5.3 GHz (C-band)
SAR resolution	26 m
SAR swath width	99 km
Scatterometer resolution	47 km
Scatterometer swath width	613 km (fore and aft) 809 km (mid)

Mission: payload all-weather high-resolution images of land and ocean, windspeed and direction, ice mapping, pollution monitoring.

RA (Radar Altimeter)

Frequency	13.8 GHz (Ku-band)
Accuracy (wave height)	+/- 0.5 m
Altitude accuracy	0.1 m

Mission: windspeed and sea surface elevation, ice sheet topography.

ATSR (Along-Track Scanning Radiometer)

Wavelengths	1.6, 3.7, 10.8 and 12.0 µm
Accuracy (sea surface temperature)	+/- 0.5 K

Mission: images of sea surface temperature, total water vapour content of atmosphere, cloud, aerosols, haze, land and ice surface emissivity.

Microwave Sounder

Frequency	23.8 and 36.5 GHz
Altitude accuracy	0.02 m
Telemetry/data	S-band

Also equipped with Laser Reflectometer (LR), Precise Range and Range-rate Equipment (PRARE) and Instrument Data Handling and Transmission (IDHT).


 ERS 2

General

Designation	23560 / 95021A
Launch date	21 Apr 1995
Country of origin	Europe
Mission	Remote sensing
Perigee/Apogee	783/786 km
Inclination	98.6°
Period	100.5 min
Launch vehicle	Ariane V72

Cost: FF3.1 billion including FF2 billion for the satellite. The launch was not insured

Technical data

Specifications

Prime contractor	Dornier
Platform	Spot (Matra)
Mass at launch	2500 kg
Payload mass	1100 kg
Dry mass	2080 kg
Length	11.8 m
Solar array	11.7 x 2.4 m
SAR antenna	10 x 1 m
Radar altimeter	1.2 m (diameter)
Stabilization	3 axis
DC power	2500 W
Design lifetime	3 years
AMI (Active Microwave Instrument)

Frequency	5.3 GHz (C-band)
SAR resolution	26 m
SAR swath width	99 km
Scatterometer resolution	47 km
Scatterometer swath width	613 km (fore and aft) 809 km (mid)

Mission: payload all-weather high-resolution images of land and ocean, windspeed and direction, ice mapping, pollution monitoring.

RA (Radar Altimeter)

Frequency	13.8 GHz (Ku-band)
Accuracy (wave height)	+/- 0.5 m
Altitude accuracy	0.1 m

Mission: windspeed and sea surface elevation, ice sheet topography.

ATSR (Along-Track Scanning Radiometer)

Wavelengths	1.6, 3.7, 10.8 and 12.0 µm
Accuracy (sea surface temperature)	+/- 0.5 K

Mission: images of sea surface temperature, total water vapour content of atmosphere, cloud, aerosols, haze, land and ice surface emissivity.

Microwave Sounder

Frequency	23.8 and 36.5 GHz
Altitude accuracy	0.02 m
GOME (Global Ozone Monitoring Experiment)

Waveband	0.24-0.79 µm
Resolution	40 x 40 km max. (horizontal) 1 km (vertical)
Swath width	120-960 km

Mission: stratospheric and tropospheric ozone profiles, cloud distribution and surface spectral reflection.

Also equipped with Laser Reflectometer (LR), Precise Range and Range-rate Equipment (PRARE) and Instrument Data Handling and Transmission (IDHT). The on board tape recorder (6.5 gigabit) can store data from a full orbit.

The telemetry is sent in S-band. The scientific data and a replication of the telemetry is sent on 2 X-band transponders.


 ESA-Geos 1

General

Designation	09931 / 77029A
Launch date	20 Apr 1977
Country of origin	Europe
Mission	Scientific: magnetosphere study
Perigee/Apogee	2767/38389 km
Inclination	26.8°
Period	734.1 min
Launch vehicle	Thor Delta #130


 ESA-Geos 2

General

Designation	10981 / 78071A
Launch date	14 Jul 1978
Country of origin	Europe
Mission	Scientific: magnetosphere study
Perigee/Apogee	36020/36061 km
Inclination	11.8°
Period	1449.1 min
Launch vehicle	Thor Delta #143


 Program: Esro

European Science Research Organisation

First European scientific program


Program: Esro

Esro 1A

Esro 1B

Esro 2B

Esro 4


 Esro 1A

Also called Aurorae

General

Designation	03459 / 68084A
Launch date	3 Oct 1968
Country of origin	Europe
Mission	Scientific: ionosphere study
Perigee/Apogee	258/1538 km
Inclination	93.8°
Period	103 min
Launch vehicle	Scout #65
Mass at launch	86 kg

Aimed to study auroras and involved phenomenons.

End of life

Decay	26 Jun 1970


 Esro 1B

Also called Boreas

General

Designation	04114 / 69083A
Launch date	1 Oct 1969
Country of origin	Europe
Mission	Scientific: ionosphere study
Perigee/Apogee	298/378 km
Inclination	85°
Period	91.3 min
Launch vehicle	Scout #66
Mass at launch	85 kg

Aimed to study auroras and involved phenomenons.

End of life

Decay	23 Nov 1969


 Esro 2B

Also called Iris

General

Designation	03233 / 68041A
Launch date	17 May 1968
Country of origin	Europe
Mission	Scientific: ionosphere study
Perigee/Apogee	334/1085 km
Inclination	97.2°
Period	99 min
Launch vehicle	Scout #62
Mass at launch	86 kg

Aimed to study cosmic rays, solar X-rays and the radiation belts around the Earth.

End of life

Decay	8 May 1971


 Esro 4

General

Designation	06285 / 72092A
Launch date	22 Nov 1972
Country of origin	Europe
Mission	Scientific: ionosphere study
Perigee/Apogee	245/1173 km
Inclination	91.1°
Period	99 min
Launch vehicle	Scout #82
Mass at launch	115 kg

Study of ionosphere, auroras and solar particles.

End of life

Decay	15 Apr 1974


 Program: Essa

Environmental Science Service Administration

American meteorology program. The satellites of this program are evolved Tiros with better surface resolution.


Program: Essa

Essa 1

Essa 2

Essa 3

Essa 4

Essa 5

Essa 6

Essa 7

Essa 8

Essa 9


 Essa 1

General

Designation	01982 / 66008A
Launch date	3 Feb 1966
Country of origin	United States
Mission	Meteorology
Perigee/Apogee	684/805 km
Inclination	97.8°
Period	99.7 min
Launch vehicle	Thor Delta #36
Mass at launch	138.6 kg


 Essa 2

General

Designation	02091 / 66016A
Launch date	28 Feb 1966
Country of origin	United States
Mission	Meteorology
Perigee/Apogee	1352/1412 km
Inclination	101°
Period	113.4 min
Launch vehicle	Thor Delta #37


 Essa 3

Also called TOS A

General

Designation	02435 / 66087A
Launch date	2 Oct 1966
Country of origin	United States
Mission	Meteorology
Perigee/Apogee	1383/1484 km
Inclination	101°
Period	114.5 min
Launch vehicle	Thor Delta #41


 Essa 4

Also called TOS B

General

Designation	02657 / 67006A
Launch date	26 Jan 1967
Country of origin	United States
Mission	Meteorology
Perigee/Apogee	1323/1437 km
Inclination	102°
Period	113.4 min
Launch vehicle	Thor Delta #45


 Essa 5

Also called TOS C

General

Designation	02757 / 67036A
Launch date	20 Apr 1967
Country of origin	United States
Mission	Meteorology
Perigee/Apogee	1352/1419 km
Inclination	101.9°
Period	113.5 min
Launch vehicle	Thor Delta #48


 Essa 6

Also called TOS D

General

Designation	03035 / 67114A
Launch date	10 Nov 1967
Country of origin	United States
Mission	Meteorology
Perigee/Apogee	1406/1483 km
Inclination	102.2°
Period	114.8 min
Launch vehicle	Thor Delta #54


 Essa 7

Also called TOS E

General

Designation	03345 / 68069A
Launch date	16 Aug 1968
Country of origin	United States
Mission	Meteorology
Perigee/Apogee	1429/1470 km
Inclination	101.5°
Period	114.9 min
Launch vehicle	Thor Delta #58


 Essa 8

Also called TOS F

General

Designation	03615 / 68114A
Launch date	15 Dec 1968
Country of origin	United States
Mission	Meteorology
Perigee/Apogee	1411/1461 km
Inclination	101.8°
Period	114.6 min
Launch vehicle	Thor Delta #62


 Essa 9

Also called TOS G

General

Designation	03764 / 69016A
Launch date	26 Feb 1969
Country of origin	United States
Mission	Meteorology
Perigee/Apogee	1423/1502 km
Inclination	101.4°
Period	115.2 min
Launch vehicle	Thor Delta #67


 Program: ETS

Engineering Test Satellite

Primary purpose of the Japanese ETS is to develop and prove bus technology. Operated by NASDA


Program: ETS

ETS 1

ETS 2

ETS 3

ETS 4

ETS 5

ETS 6


 ETS 1

Also called Kiku 1 which means "chrysanthemum"

General

Designation	08197 / 75082A
Launch date	9 Sep 1975
Country of origin	Japan
Mission
Perigee/Apogee	976/1103 km
Inclination	47°
Period	106 min
Launch vehicle	N
Launch site	Tanegashima
Mass at launch	82.5 kg


 ETS 2

Also called Kiku 2

General

Designation	09852 / 77014A
Launch date	23 Feb 1977
Country of origin	Japan
Mission	Telecommunications
Geostationary orbit
Launch vehicle
Launch site	Tanegashima
End of life

Out of service	yes


 ETS 3

Also called Kiku 4

General

Designation	13492 / 82087A
Launch date	3 Sep 1982
Country of origin	Japan
Mission	Telecommunications, experimental
Perigee/Apogee	966/1226 km
Inclination	44.6°
Period	107.2 min
Launch vehicle
Launch site	Tanegashima


 ETS 4

Also called Kiku 3

General

Designation	12295 / 81012A
Launch date	11 Feb 1984
Country of origin	Japan
Mission
Perigee/Apogee	240/20680 km
Inclination	28.2°
Period	362.4 min
Launch vehicle
Launch site	Tanegashima


 ETS 5

Also called Kiku 5

General

Designation	18316 / 87070A
Launch date	27 Aug 1987
Country of origin	Japan
Mission	Telecommunications
Geostationary orbit	150°E, inclined
Launch vehicle	H1
Launch site	Tanegashima

First 3 axis stabilized Japanese satellite with a built in apogee kick motor. It also carried a experimental mobile communications payload.

Technical data

Specifications

Prime contractor	Mitsubishi Electric
Platform	Mitsubishi
Mass at launch	1081 kg
Mass in orbit	550 kg
Length	3 m
Width	2.8 m
Height	2 m
Stabilization	3 axis
Design lifetime	1.5 years
L-band

Transponders	2
Power	30 W
Bandwidth	10 MHz
Coverage	Northern Pacific including Philippines, Indonesia and Australia
EIRP	23.2 dBW
Polarization
C-band

Transponders	1
Power	6 W
Bandwidth	20 MHz
Coverage	Northern Pacific (used for a link to NASDA)
EIRP
Polarization


 ETS 6

Also called Kiku 6

General

Designation	23230 / 94056A
Launch date	28 Aug 1994 at 22:10 UT
Country of origin	Japan
Mission	Telecommunications, experimental
Geostationary orbit	was expected in 153.8°E slot
Launch vehicle	H2 #2
Launch site	Tanegashima

Was designed to demonstrate amongst other things ion propulsion and liquid bi-propellant GEO orbit insertion. The payload would have supported mobile communications and inter satellite communication at radio and laser frequencies in preparation for Data Relay and Tracking Satellite systems.

In mid-1995 it was reported than successful intersatellite communication had taken place with UARS

End of life

Out of service	28 Aug 1994
Cause	Unable to reach GEO: a valve controlling the ergol input in the apogee kick motor (LAPS) was blocked
Technical data

Specifications

Prime contractor	Toshiba
Platform	Mitsubishi
Mass at launch	3800 kg
Mass in orbit	2000 kg
Dimension	3.0 x 2.0 x 2.8 m
Solar array	30 m span
Stabilization	3 axis
Design lifetime	2 years
S-band

Main transponders	1
Power	100 W
Bandwidth	20 MHz forward/10 MHz return
Coverage	5 spot beams
EIRP	31.5 dBW
Polarization
C-band

Main transponders	4
Power	8 W
Bandwidth	35 MHz
Coverage
EIRP	35 dBW
Polarization
Ka-band (20/30 GHz)

Main transponders	6
Power	10 W (TWTA)
Bandwidth	120 MHz forward/30 MHz return
Coverage
EIRP	48 dBW
Polarization
O-band (38/43 GHz)

Main transponders	1
Power	10 W (TWTA)
Bandwidth
Coverage
EIRP
Polarization


 Eureca 1

EUropean REtrievable CArrier

General

Designation	22065 / 92049B
Launch date	31 Jul 1992
Country of origin	Europe
Mission	Scientific
Perigee/Apogee	484/509 km
Inclination	28.5°
Period	94.6 min
Launch vehicle	STS 46

Eureca was an ESA scientific satellite designed to be launched and retrieved by the Space Shuttle. It carried the first European inter-orbit communications (IOC) link to be conducted with Olympus.

End of life

Decay	Retrieved by STS 57 on 1 Jul 1993
Technical data

Specifications

Prime contractor	MBB
Mass at launch	4450 kg
Payload mass	1000 kg
Dimension	4.5 x 2.3 x 2.7 m
Solar array	18 m span
Stabilization	3 axis
DC power	5000 W
Payload

Telemetry and data	S-band Ka-band (experimental/IOC)
Rates	uplink: 2 kbps downlink: 256 kbps


 Program: Eutelsat

EUropean TELecommunication SATellite, also called ECS (European Communication Satellite)

In 1979 the European Space Agency decided to build five ECS satellites whose management were given to the European organization Eutelsat. The Satellites were aimed to respond to the post and telecommunications needs and to transmit EBU's TV channels. To avoid frequencies attribution problems in C-band the satellites were designed to operate in Ku-band. The OTS program had provided test transmissions with small Earth stations using on board powerful transponders.

Eutelsat was officialy created in 1985. The initial mission was to complete the telephone networks without acting contrary to Intelsat laws. In fact, Eutelsat mainly makes profit with TV channels (65% of its profits).

When Eutelsat was created it gathered 17 countries. Currently 48 countries are members of Eutelsat: Albania, Andorra, Armenia, Austria, Azerbaidjan, Belarus, Belgium, Bosnia, Cyprus, Croatia, Denmark, Finland, France, Georgia, Greece, Germany, Hungary, Ireland, Iceland, Italy, Liechtenstein, Lithuania, Luxemburg, Malta, Moldavia, Monte-Carlo, Netherlands, Norway, Poland, Portugal, Rumania, Russia, San Marino, Slovaky, Sloveny, Spain, Sweden, Switzerland, Czechy, Turkey, United Kingdom, Ukraine, Vatican, Yugoslovia

Contact

Eutelsat

Tour Maine-Montparnasse, 33 avenue du Maine, 75755 Paris cedex 15, France

Tel: +33-1-4538-4747

Fax: +33-1-4538-3700

Fax on demand: +33-1-4321-2338


Program: Eutelsat

Eutelsat 1F1	Eutelsat 1F2	Eutelsat 1F3	Eutelsat 1F4
Eutelsat 1F5
Eutelsat 2F1	Eutelsat 2F2	Eutelsat 2F3	Eutelsat 2F4
Eutelsat 2F5
Hotbird 1	Hotbird 2	Hotbird 3	Hotbird 4
Hotbird 5
Eutelsat 3F1	Eutelsat 3F2	Eutelsat 3F3	Eutelsat 3 SESAT


Eutelsat 1's transponder frequency chart (GHz)

Horizontal Uplink	Horizontal Downlink	Transponder	Vertical Downlink	Vertical Uplink	Beam
	10.991667	1		14.291667	Euro/West
	11.075000	2		14.375000	East
	11.158333	3		14.458333	Euro/West
	14.491667	4		14.041667	West
	11.575000	5		14.125000	East/Atlantic
	11.658333	6		14.208333	West
14.291667		7	10.991667		Euro/West
14.375000		8	11.075000		East
14.458333		9	11.158333		Euro/West
14.041667		10	14.491667		West
14.125000		11	11.575000		Atlantic
14.208333		12	11.658333		West
	12.541667	13		14.041667	SMS
14.041667		14	12.541667		SMS

No 12 GHz transponders on 1F1


Eutelsat 1's specifications

Prime contractor	British Aerospace
Platform	ECS
Mass at launch	F1: 1050 kg Others: 1185 kg
Mass in orbit	585 kg
Payload mass	117 kg
Length	1.9 m
Width	1.4 m
Height	2.3 m
Solar array	13.8 m span
Stabilization	3 axis
DC power	EOL: 1000 W
Payload power	638.5 W
Design lifetime	7 years

Apogee kick motor: Mage 2


Eutelsat 1's Ku-band

Main transponders	10 in 11 GHz + 2 in 12 GHz (none for F1)
Backup transponders	2
Power	20 W (TWTA)
Bandwidth	72 MHz
Coverage & EIRP	Atlantic, West & East spotbeams: 46 dBW Eurobeam: 41 dBW SMS beam: 43.5 dBW (not on F1)
Polarization	linear

Only 9 transponders can be active simultaneously


Eutelsat 1's EIRP (Atlantic, West & East spots)


Eutelsat 2's EIRP (super beam)


Eutelsat 2 F1, F2 & F3's EIRP (wide beam)


Eutelsat 2F4's EIRP (wide beam)


Eutelsat 2's transponder frequency chart

Uplink frequencies	14-14.5 GHz
Downlink frequencies	10.95-11.2 GHz, 11.45-11.7 GHz and 12.5-12.75 GHz

Eutelsat 2 satellites are re-configurable in space i.e. transponders can be switched onto super or wide beam and to 11 GHz or 12 GHz.


Eutelsat 2's specifications

Prime contractor	Aerospatiale
Platform	Spacebus 100B
Mass at launch	1870 kg
Mass in orbit	915 kg
Payload mass	207.9 kg: transponders: 167.9 kg, antennas: 40 kg
Dimension	2.8 x 2.2 x 2.5 m
Solar array	22.4 m span
Stabilization	3 axis
DC power	BOL: 3000 W EOL: 2890 W
Design lifetime	10 years
Payload power	2090 W
G/T	-3.5 to +2.5 dB/K


Eutelsat 2's Ku-band

Main transponders	16
Backup transponders	8
Power	50 W (TWTA)
Bandwidth	7 transponders of 72 MHz 9 transponders of 36 MHz
Coverage & EIRP	super beam: 52 dBW wide beam: 47 dBW
Polarization	linear


Eutelsat 3's specifications (W24)

Prime contractor	Aerospatiale (with DASA, Alenia & SS/L)
Platform	Spacebus 3000
Mass at launch
Mass in orbit
Dimension
Solar array
Stabilization
DC power
Design lifetime	12-15 years

Cost: FRF 3.4 billion for the 3 satellites

2 satellites will be launched by Ariane


Eutelsat 3's Ku-band (W24)

Main transponders	24
Backup transponders
Power
Bandwidth	72 MHz
Coverage	full coverage of the entire European continent and the Mediterranean Basin steerable and fixed beams
EIRP
Polarization
Frequency	FSS band


 Eutelsat 1F1

Also called ECS 1

General

Designation	14128 / 83058A
Launch date	16 Jun 1983
Country of origin	Europe
Mission	Telecommunications
Geostationary orbit	see below
Launch vehicle	Ariane L06

Inclined since Sep 1989. Two transponders still in service: 10 & 12

Location

Begin	End	Position
L: 16 Jun 1983	Oct 1983	10°E
12 Oct 1983	Oct 1988	13°E
Oct 1988	Nov 1991	16°E
Dec 1991	Feb 1992	17.5°E
late-1992	Jul 1993	25.5°E
Sep 1993		48°E, inclined
Technical data

Specifications

Ku-band

Transponder frequency chart

EIRP spot beams coverage (dBW)

Beacon: 11.451091 GHz

This satellite was not as efficient as other Eutelsat 1 series. It could only use 6 transponders during an eclipse.


Eutelsat 1F1's EIRP (Atlantic, East & West spots)


 Eutelsat 1F2

General

Designation	15158 / 84081A
Launch date	4 Aug 1984
Country of origin	Europe
Mission	Telecommunications
Geostationary orbit	see below
Launch vehicle	Ariane V10
Location

Begin	End	Position
L: 4 Aug 1984	Sep 1990	7°E
late-1990	Feb 1992	4°E
late-1992	late-1992	2°E
Jun 1993	Dec 1993	1°E
End of life

Out of service	December 1993
Cause	End of life, moved to the junk orbit Broadcast 634,969 hours
Technical data

Specifications

Ku-band

Transponder frequency chart

Beacon: 11.45035 GHz


 Eutelsat 1F3

End of life

Out of service	13 Sep 1985
Cause	Ariane V15 explosion


 Eutelsat 1F4

General

Designation	18351 / 87078B
Launch date	16 Sep 1987
Country of origin	Europe
Mission	Telecommunications
Geostationary orbit	see below
Launch vehicle	Ariane V19

In inclined orbit since mid-May 1993. Transponders 1, 5, 7, 8, 9, 10, 11 and 12 have failed.

Location

Begin	End	Position
L: 16 Sep 1987	Oct 1988	10°E
25 Oct 1988	Oct 1990	13°E
16 Oct 1990	Oct 1992	7°E
Oct 1992	late-1992	36°E
May 1993		25.5°E, inclined
Technical data

Specifications

Ku-band

Transponder frequency chart

Beacon: 11.44965 GHz

EIRP coverage (dBW)

Spot beams

Eurobeam

SMS


Eutelsat 1F4's EIRP (Atlantic, East & West spots)


Eutelsat 1F4's EIRP (Eurobeam)


Eutelsat 1F4's EIRP (SMS beam)


 Eutelsat 1F5

General

Designation	19331 / 88063B
Launch date	21 Jul 1988
Country of origin	Europe
Mission	Telecommunications
Geostationary orbit	see below
Launch vehicle	Ariane V24

In inclined orbit since 1 Aug 1994. Transponders 3, 4, 6 and 8 have failed.

Location

Begin	End	Position
L: 21 Jul 1988	Oct 1988	10°E, tests
14 Oct 1988	Apr 1991	10°E
15 Apr 1991		21.5°E, inclined
Technical data

Specifications

Ku-band

Transponder frequency chart

Beacon: 11.44895 GHz

EIRP coverage (dBW)

Spot beams

Eurobeam

SMS


Eutelsat 1F5's EIRP (Atlantic, East & West spots)


Eutelsat 1F5's EIRP (Eurobeam)


Eutelsat 1F5's EIRP (SMS beam)


 Eutelsat 2F1

General

Designation	20777 / 90079B
Launch date	30 Aug 1990
Country of origin	Europe
Mission	Telecommunications
Geostationary orbit	13°E
Launch vehicle	Ariane V38

Operational since 24 Sep 1990.

Technical data

Specifications

Ku-band

Transponder frequency chart

EIRP coverage (dBW)

Wide beam

Super beam

Beacons: 11.451091 GHz and 12.541667 GHz

Transponder frequency chart (GHz)

Horizontal Uplink	Transponder	Vertical Downlink
10.971	20A
	25A	10.986
11.005	20B
	25B	11.016
	26A	11.049
11.055	21A
	26B	11.080
11.095	21B
	27A	11.133
11.146	22A
	27B	11.163
11.181	22B
11.554	32
	37	11.575
11.595	33
	38	11.615
11.638	34A
	39	11.658
11.675	34B
12.521	40
	45	12.542
12.563	41
	46	12.583
12.604	42
	47	12.625
12.645	43
	48	12.666
12.688	44A
	49	12.708
12.728	44B


 Eutelsat 2F2

General

Designation	21056 / 91003B
Launch date	15 Jan 1991
Country of origin	Europe
Mission	Telecommunications
Geostationary orbit	10°E
Launch vehicle	Ariane V41

Test were conducted in 21.5°E slot, operational since 8 Mar 1991

Technical data

Specifications

Ku-band

Transponder frequency chart

Beacons: 11.451820 and 12.541667 GHz

EIRP coverage (dBW)

Wide beam

Super beam

Transponder frequency chart (GHz)

Horizontal Downlink	Transponder	Vertical Downlink
	25A	10.971
10.986	20A
	25B	11.005
11.016	20B
11.049	21A
	26A	11.055
11.080	21B
	26B	11.095
11.130	22A
	27A	11.146
11.164	22B
	27B	11.181
11.554	32
	37	11.575
11.595	33
	38	11.615
11.638	34A
	39	11.658
11.675	34B
12.521	40
	45	12.542
12.562	41
	46	12.583
12.604	42
	47	12.625
12.645	43
	48	12.666
12.688	44A
	49	12.708
12.728	44B


 Eutelsat 2F3

General

Designation	21803 / 91083A
Launch date	7 Dec 1991
Country of origin	Europe
Mission	Telecommunications
Geostationary orbit	16°E
Launch vehicle	Atlas Centaur

Operational since 10 Jan 1992.

Technical data

Specifications

Ku-band

Transponder frequency chart

EIRP coverage (dBW)

Wide beam

Super beam

Beacons: 11.452570 and 12.541667 GHz

Equipped with an S400 apogee engine

Transponder frequency chart (GHz)

Horizontal Downlink	Transponder	Vertical Downlink
	25A	10.971
10.986	20A
	25B	11.005
11.016	20B
11.049	21A
	26A	11.055
11.080	21B
	26B	11.095
11.130	22A
	27A	11.146
11.164	22B
	27B	11.181
11.554	32
	37	11.575
11.595	33
	38	11.615
11.638	34A
	39	11.658
11.675	34B
12.521	40
	45	12.542
12.562	41
	46	12.583
12.604	42
	47	12.625
12.645	43
	48	12.666
12.688	44A
	49	12.708
12.728	44B


 Eutelsat 2F4

General

Designation	22028 / 92041B
Launch date	9 Jul 1992
Country of origin	Europe
Mission	Telecommunications
Geostationary orbit	7°E
Launch vehicle	Ariane V51

Operational since 18 Sep 1992.

Technical data

Specifications

Ku-band

Transponder frequency chart

EIRP coverage (dBW)

Wide beam

Super beam

Beacons: 11.451091 and 12.541667 GHz

Transponder frequency chart (GHz)

Horizontal Uplink	Transponder	Vertical Downlink
10.971	20A
	25A	10.986
11.005	20B
	25B	11.016
	26A	11.049
11.055	21A
	26B	11.080
11.095	21B
	27A	11.133
11.146	22A
	27B	11.163
11.181	22B
11.554	32
	37	11.575
11.595	33
	38	11.615
11.638	34A
	39	11.658
11.675	34B
12.521	40
	45	12.542
12.563	41
	46	12.583
12.604	42
	47	12.625
12.645	43
	48	12.666
12.688	44A
	49	12.708
12.728	44B


 Eutelsat 2F5

End of life

Out of service	24 Jan 1994
Cause	Ariane V63 failure

Was aimed to serve the eastern members in slot 36°E.

Cost: $200 million


 Hotbird 1

Also called Eutelsat 2F6

General

Designation	23537 / 95016B
Launch date	28 Mar 1995
Country of origin	Europe
Mission	Telecommunications
Geostationary orbit	13°E
Launch vehicle	Ariane V71
Technical data

Specifications

EIRP coverage (dBW)

Beacon: 11.44961 GHz horizontal

Ku-band (11.2-11.56 GHz)

Main transponders	16
Backup transponders	8
Power	70 W (TWTA)
Bandwidth	36 MHz
Coverage and EIRP	super wide beam: 49 dBW
Polarization	linear
Uplink	12.89-13.25 GHz
Transponder frequency chart (GHz)

Horizontal Downlink	Transponder	Vertical Downlink
11.221	1
	2	11.242
11.262	3
	4	11.283
11.304	5
	6	11.325
11.345	7
	8	11.366
11.387	9
	10	11.408
11.428	11
	12	11.449
11.471	13
	14	11.492
11.513	15
	16	11.534


Hotbird 1's EIRP


 Hotbird 2

General

Designation
Launch date	planned in Aug 1996
Country of origin	Europe
Mission	Telecommunications
Geostationary orbit	13°E
Launch vehicle	Atlas 2A
Launch site
Technical data

Specifications

Prime contractor	Matra Marconi Space
Platform	Eurostar 2000 augmented
Mass at launch
Payload mass	268 kg: transponders: 192 kg, antennas: 76 kg
Dimension	2.5 x 1.7 x 2.6 m
Stabilization	3 axis
DC power	equinox: 5500 W, solstice: 4988 W
Payload power	4188 W
Design lifetime	12-15 years
Ku-band (11.45-11.7 GHz & 11.7-12.5 GHz)

Main transponders	20
Backup transponders	10
Power	110 W (TWTA)
Bandwidth	20 transponders of 33 MHz (12 GHz) 5 transponders of 36 MHz (11 GHz) 1 transponder of 72 MHz (11 GHz) 1 transponder of 72 MHz (12.5 GHz)
Coverage	super beam: Europe from West to East wide beam: from the Canary Islands to the republics South of Russia and Gulf countries Transponders switchable one by one on each zone (footprints in TS 12/95)
EIRP	Superbeam: 52 dBW Widebeam: 49 dBW
Polarization	linear

6 transponders in 12 GHz can be switched in 11 GHz and the 36 MHz transponders can be operated in half-transponder mode.

Uplink: 13.8-14.0 GHz and 17.3-18.1 GHz

Transponder frequency chart (GHz)

Horizontal Downlink	Transponder	Vertical Downlink	Bandwidth
11.554410	D1		36 MHz
	D2	11.575160	36 MHz
11.595910	D3		36 MHz
	D4	11.616660	36 MHz
11.658333	D5		72 MHz
	D6	11.658160	36 MHz
	E1	11.727480	33 MHz
11.746660	E2		33 MHz
	E3	11.765840	33 MHz
11.785020	E4		33 MHz
	E5	11.804200	33 MHz
11.823380	E6		33 MHz
	E7	11.842560	33 MHz
11.861740	E8		33 MHz
	E9	11.880920	33 MHz
11.900100	E10		33 MHz
	E11	11.919280	33 MHz
11.938460	E12		33 MHz
	E13	11.957640	33 MHz
11.976820	E14		33 MHz
	E15	11.996000	33 MHz
12.015180	E16		33 MHz
	E17	12.034360	33 MHz
12.053540	E18		33 MHz
	E19	12.072720	33 MHz
12.091900	E20		33 MHz


 Hotbird 3

will be launched by Ariane in early 1997

should have a spot to South Africa

20 Ku-band transponders

Possible frequency bands:

(14.0-14.25 / 12.5-12.75 GHz), (14.25-14.5 / 10.95-11.2 GHz) & (17.69-18.1 / 12.09-12.5 GHz)

(footprints in TS 12/95)


 Hotbird 4

will be launched by Ariane in late 1997

built by MMS

20 Ku-band transponders, based on a Eurostar 2000 platform

cost: FRF 1.4 billion

Lifetime = 12 - 15 years

(footprints in TS 12/95)


 Hotbird 5

ordered in February 1996 to replace Eutelsat 2F1


 Eutelsat 3F1

General

Designation
Launch date	planned in Mar 1998
Country of origin	Europe
Mission	Telecommunications
Geostationary orbit	7°E
Launch vehicle
Launch site

The replaced satellite will be located at either 21.5°E, 25.5°E or 36°E

Technical data

Specifications

Ku-band


 Eutelsat 3 SESAT

General

Designation
Launch date	planned in May 1998
Country of origin	Europe
Mission	Telecommunications
Geostationary orbit	48°E
Launch vehicle	Proton

Cost: FRF 845 million

Technical data

Specifications

Prime contractor	NPO-PM with Alcatel Espace
Platform	Siberian platform
Mass at launch	2.3-3 tons
Mass in orbit
Dimension
Solar array
Stabilization
DC power
Design lifetime	7-10 years
Ku-band

Main transponders	18
Backup transponders
Power
Bandwidth
Coverage
EIRP
Polarization

French payload


 Eutelsat 3F2

General

Designation
Launch date	planned in Sep 1998
Country of origin	Europe
Mission	Telecommunications
Geostationary orbit	10°E
Launch vehicle
Launch site

The replaced satellite will be located at either 21.5°E, 25.5°E or 36°E

Technical data

Specifications

Ku-band


 Eutelsat 3F3

General

Designation
Launch date	planned in Apr 1999
Country of origin	Europe
Mission	Telecommunications
Geostationary orbit	16°E
Launch vehicle
Launch site

The replaced satellite will be located at either 21.5°E, 25.5°E or 36°E

Technical data

Specifications

Ku-band


 EUVE

Extreme Ultra Violet Explorer

General

Designation	21987 / 92031A
Launch date	7 Jun 1992
Country of origin	United States
Mission	Scientific: Astronomy
Perigee/Apogee	503/527 km
Inclination	28.4°
Period	94.9 min
Launch vehicle	Delta 2 #210

Based on the MultiMission Spacecraft bus


Exos
 Program: Exos

Japanese scientific program


Program: Exos

Exos A

Exos B

Exos C

Exos D


 Exos A

Also called Kyokko which means "aurora"

General

Designation	10664 / 78014A
Launch date	4 Feb 1978
Country of origin	Japan
Mission	Scientific: ionosphere study
Perigee/Apogee	634/3957 km
Inclination	65.4°
Period	134 min
Launch vehicle	Mu 3H
Launch site	Kagoshima
Mass at launch	103 kg


 Exos B

Also called Jikiken which means "magnetosphere"

General

Designation	11027 / 78087A
Launch date	16 Sep 1978
Country of origin	Japan
Mission	Scientific: magnetophere study
Perigee/Apogee	246/21151 km
Inclination	31.4°
Period	370.2 min
Launch vehicle	Mu 3H
Launch site	Kagoshima
Mass at launch	92 kg

Initial orbit: probably 230 km x 30558 km x 31° x 525 min


 Exos C

Also called Ohzora which means "sky"

General

Designation	14722 / 84015A
Launch date	14 Feb 1984
Country of origin	Japan
Mission	Scientific: high atmosphere study
Perigee/Apogee	247/331 km
Inclination	74.6°
Period	90.3 min
Launch vehicle	Mu 3S1
Launch site	Kagoshima
Mass at launch	210 kg
End of life

Decay	19 Jul 1989


 Exos D

Also called Akebono

General

Designation	19822 / 89016A
Launch date	21 Feb 1989
Country of origin	Japan
Mission	Scientific: magnetosphere and ionosphere study
Perigee/Apogee	264/8501 km
Inclination	75.1°
Period	185.2 min
Launch vehicle	Mu 3S 2
Launch site	Kagoshima
Mass at launch	300 kg


 Exosat

General

Designation	14095 / 83051A
Launch date	26 May 1983
Country of origin	Europe
Mission	Scientific: astronomy
Perigee/Apogee	340/191878 km
Inclination	72.5°
Period	5442.1 min
Launch vehicle	Thor Delta #169
Mass at launch	510 kg

Astronomy satellite designed to map the position and characteristics of cosmic X-ray sources. The observatory performed some 2000 observations during its operational lifetime.

End of life

Out of service	9 Apr 1986
Decay	6 May 1986
Technical data

Specifications

Prime contractor	MBB
Platform
Mass at launch	500 kg
Payload mass	120 kg
Diameter	2.1 m
Height	1.35 m
Solar array	1.85 x 2 m
Stabilization	3 axis
DC power	EOL: 260 W
Design lifetime	2 years
Telemetry/data	S-band (6 W): 8 kbps
Low energy experiment: 2 grazing incidence (imaging) telescopes

Field of view	1°
Collecting area	90 cm²
Medium energy experiment: 8 proportional counters

Field of view	1.5°
Collecting area	1800 cm²
Gas scintillator spectrometer

Field of view	1.5°
Collecting area	200 cm²
X-ray energy rate	low energy 0.04-2 keV medium energy 1.5-50 keV spectrometer 2-80 keV


 Program: Explorer

American scientific program operated by the US Army.

Beginning of the program

Date	Launch date	Launch vehicle
31 Jan 1958	Explorer 01	Jupiter C
5 Mar 1958	Failure	Jupiter C
26 May 1958	Explorer 03	Jupiter C
26 Jul 1958	Explorer 04	Jupiter C
24 Aug 1958	Failure	Jupiter C
22 Oct 1958	Failure	Jupiter C
16 Jul 1959	Failure	Juno 2
14 Aug 1959	Failure	Juno 2
13 Oct 1959	Explorer 07	Juno 2
Sub programs

AD (Air Density)

ADE (Atmospheric Density Explorer)

AE (Atmosphere Explorer)

EPE (Energetic Particules Explorer)

GEOS (Geodetic Earth Orbiting Satellite)

IE (Ionosphere Explorer)

IMP (Interplanetary Monitoring Probes)


Program: Explorer

Explorer 01 Explorer 03 Explorer 04 Explorer 06 Explorer 07 Explorer 08 Explorer 09 Explorer 10 Explorer 11 Explorer 12 Explorer 13 Explorer 14 Explorer 15	Explorer 16 Explorer 17 Explorer 18 Explorer 19 Explorer 20 Explorer 21 Explorer 22 Explorer 23 Explorer 24 Explorer 25 Explorer 26 Explorer 27 Explorer 28	Explorer 29 Explorer 30 Explorer 31 Explorer 32 Explorer 33 Explorer 34 Explorer 36 Explorer 38 Explorer 39 Explorer 40 Explorer 41 Explorer 42 Explorer 43	Explorer 45 Explorer 46 Explorer 47 Explorer 48 Explorer 50 Explorer 51 Explorer 52 Explorer 53 Explorer 54 Explorer 55


 Explorer 01

General

Designation	00004 / 58001A
Launch date	1 Feb 1958
Country of origin	United States
Mission	Scientific: ionosphere study
Perigee/Apogee	347/1859 km
Inclination	33.2°
Period	107.2 min
Launch vehicle	Jupiter C (Juno 1 from the US Army, 18 t, 21 m tall, 4 stages)
Launch site	Cape Canaveral
Mass at launch	14.6 kg

Rocked realized by Wernher von Braun's team, a german engineer from Peenemünde. He had been working since 1953 at the Redstone Arsenal (Huntsville, Alabama) to design a balistic missile with the help of the Army Ballistic Missile Agency and the Jet Propulsion Laboratory.

First American satellite: height 1.2 m, diameter 20 cm. It was in fact the 4th stage of the rocket. Carrying 5 kg of instruments (batteries, radio transmitter, Geiger counter).

Has discovered Van Allen belts (radiations belts around the Earth) because the orbit was more excentric than expected.

End of life

Out of service	23 May 1958
Decay	31 Mar 1970 in Southern Pacific


 Explorer 03

General

Designation	00006 / 58003A
Launch date	26 Mar 1958
Country of origin	United States
Mission	Scientific: ionosphere study
Perigee/Apogee	186/2799 km
Inclination	33.4°
Period	115.7 min
Launch vehicle	Jupiter C
Launch site	Cape Canaveral
End of life

Decay	28 Jun 1958


 Explorer 04

General

Designation	00009 / 58005A
Launch date	26 Jul 1958
Country of origin	United States
Mission	Scientific: ionosphere study
Perigee/Apogee	257/1352 km
Inclination	50.2°
Period	100.9 min
Launch vehicle	Jupiter C
Launch site	Cape Canaveral
End of life

Decay	23 Oct 1959


 Explorer 06

Also called S 2

General

Designation	00015 / 59004A
Launch date	7 Aug 1959
Country of origin	United States
Mission	Scientific: magnetosphere study
Perigee/Apogee	245/42400 km
Inclination	47°
Period	765 min
Launch vehicle	Thor Able
Launch site	Cape Canaveral
End of life

Decay	30 Jun 1961


 Explorer 07

General

Designation	00022 / 59009A
Launch date	13 Oct 1959
Country of origin	United States
Mission	Scientific: high atmosphere study
Perigee/Apogee	524/855 km
Inclination	50.3°
Period	98.6 min
Launch vehicle	Juno 2
Launch site	Cape Canaveral
Mass at launch	45 kg


 Explorer 08

General

Designation	00060 / 60014A
Launch date	3 Nov 1960
Country of origin	United States
Mission	Scientific: ionosphere study
Perigee/Apogee	394/1331 km
Inclination	49.9°
Period	102.2 min
Launch vehicle
Launch site	Cape Canaveral
Mass at launch	45 kg

First NASA satellite


 Explorer 09

General

Designation	00081 / 61004A
Launch date	16 Feb 1961
Country of origin	United States
Mission	Scientific: high atmosphere study
Perigee/Apogee	757/2433 km
Inclination	38.8°
Period	118 min
Launch vehicle	Scout #4
End of life

Decay	9 Apr 1964


 Explorer 10

Also called P-14

General

Designation	00098 / 61010A
Launch date	25 Mar 1961
Country of origin	United States
Mission
Perigee/Apogee	221/181100 km
Inclination	33°
Period	5013.9 min
Launch vehicle	Thor Delta #4
End of life

Decay	30 Jun 1961


 Explorer 11

General

Designation	00107 / 61013A
Launch date	27 Apr 1961
Country of origin	United States
Mission	Scientific: gamma-ray astronomy
Perigee/Apogee	480/1458 km
Inclination	28.8°
Period	104.5 min
Launch vehicle
Launch site	Cape Canaveral


 Explorer 12

Also called EPE A

General

Designation	00170 / 61020A
Launch date	16 Aug 1961
Country of origin	United States
Mission	Scientific: magnetosphere study
Perigee/Apogee	790/79920 km
Inclination	33.4°
Period	1587.3 min
Launch vehicle	Thor Delta #6
End of life

Decay	30 Sep 1963


 Explorer 13

Also called S 55A

General

Designation	00180 / 61022A
Launch date	25 Aug 1961
Country of origin	United States
Mission	Scientific: observation of meteorites
Perigee/Apogee	125/1164 km
Inclination	37.7°
Period	97.5 min
Launch vehicle	Scout #6
End of life

Decay	28 Aug 1961


 Explorer 14

Also called EPE B and S 3A

General

Designation	00432 / 62051A
Launch date	2 Oct 1962
Country of origin	United States
Mission	Scientific: magnetosphere study
Perigee/Apogee	915/96959 km
Inclination	33.6°
Period	2157.9 min
Launch vehicle	Thor Delta #13
End of life

Decay	1 Jul 1966


 Explorer 15

Also called EPE C and S 3B

General

Designation	00445 / 62059A
Launch date	27 Oct 1962
Country of origin	United States
Mission
Perigee/Apogee	306/17610 km
Inclination	17.9°
Period	314.7 min
Launch vehicle	Thor Delta #14
End of life

Decay	19 Dec 1978


 Explorer 16

Also called S 55

General

Designation	00506 / 62070A
Launch date	16 Dec 1962
Country of origin	United States
Mission	Scientific: observation of meteorites
Perigee/Apogee	744/1159 km
Inclination	52°
Period	104.1 min
Launch vehicle	Scout #14


 Explorer 17

Also called AE A

General

Designation	00564 / 63009A
Launch date	3 Apr 1963
Country of origin	United States
Mission	Scientific: high atmosphere study
Perigee/Apogee	254/891 km
Inclination	57.6°
Period	96.1 min
Launch vehicle	Thor Delta #17
End of life

Decay	24 Nov 1966


 Explorer 18

Interplanetary Monitoring Probe, also called IMP 01

General

Designation	00693 / 63046A
Launch date	27 Nov 1963
Country of origin	United States
Mission	Scientific: magnetosphere study
Perigee/Apogee	192/197616 km
Inclination	33.3°
Period	5666.2 min
Launch vehicle	Thor Delta #21
End of life

Decay	30 Dec 1965


 Explorer 19

Atmospheric Density Explorer, also called ADE A

General

Designation	00714 / 63053A
Launch date	19 Dec 1963
Country of origin	United States
Mission	Scientific: high atmosphere study
Perigee/Apogee	597/2391 km
Inclination	78.6°
Period	115.9 min
Launch vehicle	Scout #24

Sphere in aluminum (3.65 m diameter, 7 to 9 kg)

End of life

Decay	10 May 1981


 Explorer 20

Also called IE A

General

Designation	00870 / 64051A
Launch date	25 Aug 1964
Country of origin	United States
Mission	Scientific: ionosphere study
Perigee/Apogee	855/1001 km
Inclination	79.9°
Period	103.6 min
Launch vehicle	Scout #30


 Explorer 21

Interplanetary Monitoring Probe, also called IMP 02

General

Designation	00889 / 64060A
Launch date	4 Oct 1964
Country of origin	United States
Mission	Scientific: magnetosphere study
Perigee/Apogee	191/95590 km
Inclination	33.5°
Period	2097 min
Launch vehicle	Thor Delta #26
End of life

Decay	30 Jan 1966


 Explorer 22

Also called Beacon B

General

Designation	00899 / 64064A
Launch date	10 Oct 1964
Country of origin	United States
Mission	Scientific: Geodesy and ionosphere study
Perigee/Apogee	872/1053 km
Inclination	79.7°
Period	104.3 min
Launch vehicle	Scout #32


 Explorer 23

Also called S 55C

General

Designation	00924 / 64074A
Launch date	6 Nov 1964
Country of origin	United States
Mission	Scientific: observation of meteorites
Perigee/Apogee	463/980 km
Inclination	51.9°
Period	99.2 min
Launch vehicle	Scout #33
End of life

Decay	29 Jun 1983


 Explorer 24

Atmospheric Density Explorer, also called ADE B

General

Designation	00931 / 64076A
Launch date	21 Nov 1964
Country of origin	United States
Mission	Scientific: high atmosphere study
Perigee/Apogee	530/2498 km
Inclination	81.4°
Period	116.3 min
Launch vehicle	Scout #34

Sphere in aluminum (3.65 m diameter, 7 to 9 kg)

End of life

Decay	18 Oct 1968


 Explorer 25

Also called Injun 4

General

Designation	00932 / 64076B
Launch date	21 Nov 1964
Country of origin	United States
Mission	Scientific: ionosphere study
Perigee/Apogee	524/2349 km
Inclination	81.4°
Period	114.6 min
Launch vehicle	Scout #34


 Explorer 26

Also called EPE D

General

Designation	00963 / 64086A
Launch date	21 Dec 1964
Country of origin	United States
Mission	Scientific: ionosphere study
Perigee/Apogee	284/10043 km
Inclination	19.8°
Period	205.7 min
Launch vehicle	Thor Delta #27


 Explorer 27

Also called Beacon C

General

Designation	01328 / 65032A
Launch date	29 Apr 1965
Country of origin	United States
Mission	Scientific: Geodesy and ionosphere study
Perigee/Apogee	932/1309 km
Inclination	41.2°
Period	107.7 min
Launch vehicle	Scout #36


 Explorer 28

Interplanetary Monitoring Probe, also called IMP 03

General

Designation	01388 / 65042A
Launch date	29 May 1965
Country of origin	United States
Mission	Scientific: magnetosphere study
Perigee/Apogee	229/261206 km
Inclination	30.5°
Period	8419.7 min
Launch vehicle	Thor Delta #31
End of life

Decay	4 Jul 1968


 Explorer 29

Also called Geos 1

General

Designation	01726 / 65089A
Launch date	6 Nov 1965
Country of origin	United States
Mission	Scientific: geodesy
Perigee/Apogee	1114/2273 km
Inclination	59.4°
Period	120.3 min
Launch vehicle	Thor Delta #34
Mass at launch	175 kg


 Explorer 30

Also called IQSY

General

Designation	01738 / 65093A
Launch date	19 Nov 1965
Country of origin	United States
Mission
Perigee/Apogee	667/871 km
Inclination	59.7°
Period	100.2 min
Launch vehicle	Scout #38


 Explorer 31

Also called DME A

General

Designation	01806 / 65098B
Launch date	29 Nov 1965
Country of origin	United States
Mission	Scientific: ionosphere study
Perigee/Apogee	502/2857 km
Inclination	79.8°
Period	120 min
Launch vehicle	Thor Agena B
Launch site	Vandenberg


 Explorer 32

Also AE B

General

Designation	02183 / 66044A
Launch date	25 May 1966
Country of origin	United States
Mission	Scientific: high atmosphere study
Perigee/Apogee	282/2723 km
Inclination	64.6°
Period	116 min
Launch vehicle	Thor Delta #38
End of life

Decay	22 Feb 1985


 Explorer 33

Interplanetary Monitoring Probe, also called IMP 04

General

Designation	02258 / 66058A
Launch date	1 Jul 1966
Country of origin	United States
Mission
Perigee/Apogee	85228/481417 km
Inclination	40.9°
Period	25863.5 min
Launch vehicle	Thor Delta #39


 Explorer 34

Interplanetary Monitoring Probe, also called IMP 05

General

Designation	02817 / 67051A
Launch date	24 May 1967
Country of origin	United States
Mission
Perigee/Apogee	242/214379 km
Inclination	67.1°
Period	6358.2 min
Launch vehicle	Thor Delta #49
End of life

Decay	3 May 1969


 Explorer 36

Also called Geos 2

General

Designation	03093 / 68002A
Launch date	11 Jan 1968
Country of origin	United States
Mission	Scientific: geodesy
Perigee/Apogee	1079/1572 km
Inclination	105.8°
Period	112.2 min
Launch vehicle	Thor Delta #56


 Explorer 38

Also called RAE 1

General

Designation	03307 / 68055A
Launch date	4 Jul 1968
Country of origin	United States
Mission	Scientific: radio-astronomy
Perigee/Apogee	5835/5861 km
Inclination	120.9°
Period	224.3 min
Launch vehicle	Thor Delta #57


 Explorer 39

Atmospheric Density Explorer, also called ADE C

General

Designation	03337 / 68066A
Launch date	8 Aug 1968
Country of origin	United States
Mission	Scientific: high atmosphere study
Perigee/Apogee	670/2538 km
Inclination	80.7°
Period	118.3 min
Launch vehicle	Scout #63

Sphere in aluminum (3.65 m diameter, 7 to 9 kg)

End of life

Decay	22 Jun 1981


 Explorer 40

Also called Injun 5

General

Designation	03338 / 68066B
Launch date	8 Aug 1968
Country of origin	United States
Mission	Scientific: ionosphere study
Perigee/Apogee	677/2494 km
Inclination	80.7°
Period	117.9 min
Launch vehicle	Scout #63


 Explorer 41

Interplanetary Monitoring Probe, also called IMP 07

General

Designation	03990 / 69053A
Launch date	21 Jun 1969
Country of origin	United States
Mission	Scientific: magnetosphere study
Perigee/Apogee	80374/98159 km
Inclination	86°
Period	4906.3 min
Launch vehicle	Thor Delta #69
End of life

Decay	23 Dec 1972


 Explorer 42

Also called Uhuru or SAS 1

General

Designation	04797 / 70107A
Launch date	12 Dec 1970
Country of origin	United States
Mission	Scientific: X-ray astronomy
Perigee/Apogee	521/570 km
Inclination	3°
Period	95.5 min
Launch vehicle	Scout #71
End of life

Decay	5 Apr 1979


 Explorer 43

Interplanetary Monitoring Probe, also called IMP 08

General

Designation	05043 / 71019A
Launch date	13 Mar 1971
Country of origin	United States
Mission	Scientific: magnetosphere study
Perigee/Apogee	1845/203130 km
Inclination	31.2°
Period	5957.9 min
Launch vehicle	Thor Delta #83
End of life

Decay	2 Oct 1974


 Explorer 45

Also called SSS 1

General

Designation	05598 / 71096A
Launch date	15 Nov 1971
Country of origin	United States
Mission
Perigee/Apogee	272/18149 km
Inclination	3.2°
Period	322.8 min
Launch vehicle	Scout #77
End of life

Decay	10 Jan 1992


 Explorer 46

Also called MTS

General

Designation	06142 / 72061A
Launch date	13 Aug 1972
Country of origin	United States
Mission	Scientific: observation of meteorites
Perigee/Apogee	492/811 km
Inclination	37.7°
Period	97.7 min
Launch vehicle	Scout #79
End of life

Decay	2 Nov 1979


 Explorer 47

Interplanetary Monitoring Probe, also called IMP 09

General

Designation	06197 / 72073A
Launch date	23 Sep 1972
Country of origin	United States
Mission	Scientific: magnetosphere study
Perigee/Apogee	201100/235600 km
Inclination	17.2°
Period	17670 min
Launch vehicle	Thor Delta #90


 Explorer 48

Also called SAS 2

General

Designation	06282 / 72091A
Launch date	15 Nov 1972
Country of origin	United States
Mission	Scientific: gamma-ray astronomy
Perigee/Apogee	526/526 km
Inclination	1°
Period	95.2 min
Launch vehicle	Scout #81
End of life

Decay	20 Aug 1976


 Explorer 50

Interplanetary Monitoring Probe, also called IMP 10

General

Designation	06893 / 73078A
Launch date	26 Oct 1973
Country of origin	United States
Mission	Scientific: magnetosphere study
Perigee/Apogee	141185/288857 km
Inclination	28.7°
Period	17279 min
Launch vehicle	Thor Delta #97


 Explorer 51

Also called AE C

General

Designation	06977 / 73101A
Launch date	16 Dec 1973
Country of origin	United States
Mission	Scientific: high atmosphere study
Perigee/Apogee	155/4306 km
Inclination	68.1°
Period	132.5 min
Launch vehicle	Thor Delta #99
End of life

Decay	12 Dec 1978


 Explorer 52

Also called Hawkeye

General

Designation	07325 / 74040A
Launch date	3 Jun 1974
Country of origin	United States
Mission
Perigee/Apogee	469/125569 km
Inclination	89°
Period	3032 min
Launch vehicle	Scout #87
End of life

Decay	30 Apr 1978


 Explorer 53

Also called SAS 3

General

Designation	07788 / 75037A
Launch date	7 May 1975
Country of origin	United States
Mission	Scientific: X-ray astronomy
Perigee/Apogee	498/507 km
Inclination	3°
Period	94.7 min
Launch vehicle	Scout #91
End of life

Decay	9 Apr 1979


 Explorer 54

Also called AE D

General

Designation	08353 / 75096A
Launch date	6 Oct 1975
Country of origin	United States
Mission	Scientific: high atmosphere study
Perigee/Apogee	151/3819 km
Inclination	90.1°
Period	126.8 min
Launch vehicle	Thor Delta #115
End of life

Decay	12 Mar 1976


 Explorer 55

Also called AE E

General

Designation	08440 / 75107A
Launch date	20 Nov 1975
Country of origin	United States
Mission	Scientific: high atmosphere study
Perigee/Apogee	154/3002 km
Inclination	19.7°
Period	117.7 min
Launch vehicle	Thor Delta #117
End of life

Decay	10 Jun 1981


 EXPRESS (German)

EXPeriment REentry Space System

General

Designation	none assigned
Launch date	15 Jan 1995 at 13:45 UT
Country of origin	Germany
Mission	Experimentation of materials
Perigee/Apogee	110/250 km
Inclination	33°
Period
Launch vehicle	Mu 3S 2
Launch site	Kagoshima
Mass at launch	765 kg

The payload used a Russian-built reentry vehicle and the launch was carried out by the Japanese ISAS space agency. It was due to land in the Australian desert after a five day flight, but the TVC (thrust vector control) on the second stage malfunctioned 103 seconds after launch, and the fourth stage and payload entered a 110 x 250 km x 33 deg orbit, instead of the intended 270 x 380 km one. This failure was probably due to second-stage attitude-control oscillations that exhausted attitude-control fuel. The reentry capsule decay in Ghana whereas the service module reentered over the Pacific on its second orbit of the Earth.

The reentry vehicle carried two CATEX materials processing ovens, and three German (CETEX, PYREX and RAFLEX) and one Japanese (RTEX) heat shield material reentry experiments.

End of life

Decay	15 Jan 1995


 Program: Express

Also called Glavstar

Russian telecommunication program replacing Gorizont. Satellite are owned by Informcosmos and operated by Intersputnik.

The Express slots (reservation names, not satellites) are:

Express 01	37.5°W
Express 02	14°W
Express 03	11°W
Express 04	40°E
Express 05	53°E
Express 06	80°E
Express 07	90°E
Express 08	96.5°E
Express 09	103°E
Express 10	140°E
Express 11	145°E
Express 12	155°W
Express 13	99°E


Program: Express

Express 01

Express 02


Express' specifications

Prime contractor	NPO PM
Platform	NPO Express (similar to GALS)
Mass at launch	2500 kg
Mass in orbit
Diameter	3.6 m
Height	6.1 m
Solar array	twin panels, 21 m span
Stabilization	3 axis
DC power	2000 W
Design lifetime	5 years

Equipped with an advanced Xenon ion engine that reduces the amount of propellant needed to fine-tune the initial orbit and perform station-keeping maneuvers. Beacons: 11.400 GHz (power: 0.1 W; EIRP: 14.5 dBW) and 3.800 GHz (power: 0.2 W; EIRP: 9 dBW)


Express antenna's specifications

Antenna	Frequency band	Function / Gain max	Coverage	Beam width	Steerability (degrees)
					North/South	West/East
A1	C	TX / 19.0	global	17°x17°	none	none
A2	C	TX / 30.0	spot	5°x5°	7.3/5	5.5/5.5
A3	C	TX / 20.7	quasi global	15°x15°	none	none
A4	C	TX / 26.5	elliptical	5°x11°	7.3/7.3	none
A5	C	TX / 20.7	quasi global	15°x15°	none	none
A6	C	TX / 26.5	elliptical	5°x11°	7.3/7.3	none
A7	C	RX / 19.0	global	17x17°	none	none
A8	C	RX / 26.5	elliptical	5°x11°	7.3/7.3	none
A9	Ku	RX and TX / 30.0	spot	5°x5°	7.3/5	5.5/5.5

See also the transponder/antenna connection diagram


Express' C-band

Main transponders	10
Backup transponders
Power	9 transponders of 10.5 W (TWTA) 1 transponder (#6) of 65 W (TWTA)
Bandwidth	all transponders: 34 MHz transponder #6: 40 MHz
Coverage and EIRP	transponder #6: global beam (A1): 35.6 dBW spot beam (A2): 46.1 dBW 2 quasi global beams (A3 & A5): 28.9 or 31 dBW 2 zone beams (A4 & A6): 34.7 dBW
Polarization	circular


Express' Ku-band

Main transponders	2
Backup transponders
Power	60 W (TWTA)
Bandwidth	34 MHz
Coverage and EIRP	spot beam (A9): 39.2 dBW
Polarization	linear


Express' transponder frequency chart (GHz)

C-band

LHCP Uplink	Transponder	RHCP Downlink	Comments
6.000	6	3.675	global or spot beam, 40 MHz
6.050	7	3.725	quasi global or zone beam
6.100	8	3.775	quasi global or zone beam
6.150	9	3.825	quasi global or zone beam
6.200	10	3.875	quasi global or zone beam
6.250	11	3.925	quasi global or zone beam
6.300	14	3.975	zone or spot beam
6.350	15	4.025	quasi global or zone beam
6.400	16	4.075	zone or spot beam
6.450	17	4.125	quasi global or zone beam
Ku-band

Horizontal Downlink	Transponder	Vertical Uplink
11.525	12	14.325
11.675	20	14.425


Express' transponder/antenna connections


 Express 01

General

Designation	23319 / 94067A
Launch date	13 Oct 1994 at 16:19 UT
Country of origin	CIS
Operator	Intersputnik
Mission	Telecommunications
Geostationary orbit	Express-02, 14°W
Launch vehicle	Proton #227

Test carried out in 71°E slot

Technical data

Specifications

Antenna specifications

Transponder/Antenna connections

C-band

Ku-band

Transponder Frequency Chart

EIRP coverage (dBW)

C-band, quasi-global (A3 & A5)

C-band, hemispheric (A4)

C-band, spot (A2)

Ku-band, spot (A9)


Express 01's C-band EIRP: quasi-global A3 & A5


Express 01's C-band EIRP: spot A2

Add 7.9 dBW for transponder #6


Express 01's C-band EIRP: hemispheric A4


Express 01's Ku-band EIRP: spot A9


 Express 02

General

Designation
Launch date	planned in Apr 1995
Country of origin	CIS
Mission	Telecommunications
Geostationary orbit	express-06, 80°E
Launch vehicle
Launch site

GE American Communications Inc. announced it will launch a international video programming satellite service on Intersputnik Express 6 aimed at the Indian sub-continent. The television service is expected to begin July 1. The news programming will be in English and Hindi. Also GE Americom has a long-term agreement for five C-band and two Ku-band transponders.


 Eyesat

Also called AO-27 or Amrad or Oscar 27

General

Designation	22825 / 93061C
Launch date	25 Sep 1993
Country of origin	United States
Mission	Telecommunications
Operator	Interferometrics (USA)
Perigee/Apogee	790/803 km
Inclination	98.7°
Period	100.8 min
Launch vehicle	Ariane V59

Aimed for transmiting data of localization and surveillance of industrial equipments for Interferometris.

Technical data

Specifications

Prime contractor	Associazione Radioamatori Italiani
Platform	Amsat-NA Microsat
Mass at launch	12.5 kg
Mass in orbit
Length	230 mm
Width	230 mm
Height	235 mm
Stabilization	magnetic
DC power
Design lifetime	5-7 years
Frequency chart (MHz)

Downlink freq.	Transponder/Beacon	Mode
436.800		9600 bps FSK
Uplink freq.	Transponder/Beacon	Mode
145.925		9600 bps FSK

1 station at a time


 Program: Fasat

Fuerza Aerea de chile Satellite

First Chilean satellite program. Purpose: remote sensing and telecommunication experiments

4 satellites are planned in this program


Program: Fasat

Fasat Alfa

Fasat Bravo


 Fasat Alfa

General

Designation	/ 95046? Failed to separate from Sich 1
Launch date	31 Aug 1995 at 06:50 UT
Country of origin	Chile
Operator	Chilean Air Force (FACH: Fuerza Aerea de Chile)
Mission	Remote sensing
Perigee/Apogee	1050 km, polar orbit
Inclination
Period
Launch vehicle	Tskilon 3
Launch site	Plesetsk LC32

First Chilean satellite

Investigation of the failure showed a British docking mechanism had been at fault.

The satellite carried five grams of Chilean soil on board. It was to transmit regular information on ultraviolet radiation and the ozone layer over the antarctic. It was also to image the Chilean territory and carry out educational experiments for children with informative bulletins. The other 3 experiments, which would have been regularly carried out by Fasat Alfa, would have ment working with other satellite complexes, for the transmission and storage of data and space navigation systems.

When FACH proposed the construction of the first Chilean satellite in 1993, negotiations were arranged with Mexican, U.S. and British specialists. Surrey Satellite Technology Limited (SSTL) offered the most tempting deal to the Chileans, offering joint construction of the probe, technology transfer, and postgraduate training for the FACH technicians. The satellite was built using parts built by the Chilean National Aeronautical Company (ENAER), a branch of FACH, along with space computer technology donated by the Lockheed Company of the United States for experimental purposes.

Technical data

Specifications

Prime contractor	SSTL
Platform	UOSAT
Mass at launch	50 kg
Mass in orbit
Dimension	70 x 36 x 36 cm
Solar array
Stabilization
DC power
Design lifetime	6 years

It has a six meters long stabilization beam with a weight in its tail which will unfold once in orbit.


 Fasat Bravo

General

Designation
Launch date	planned in 1996
Country of origin	Chile
Operator	Chilean Air Force (FACH: Fuerza Aerea de Chile)
Mission
Perigee/Apogee
Inclination
Period
Launch vehicle
Launch site	CIS

Built by SSTL (Uosat) This time, the system for the separation of the satellite will be Ukrainian, not British.


 Faisat

General

Designation	23465 / 95002C
Launch date	24 Jan 1995 at 03:54 UT
Country of origin	United States
Operator	Final Analysis Inc.
Mission	Experimental: communications
Perigee/Apogee	967/1021 km
Inclination	82.9°
Period	105 min
Launch vehicle	Cosmos 3C
Launch site	Plesetsk LC132
Mass at launch	115 kg

Faisat is store and forward communications satellite modified by FAI, an American company from an existing satellite bus whose mission was cancelled (probably a DARPA satellite). FAI plans to have 5 satellites operating in mid-1997.

FAI plans to launch a constellation of 26 such satellites -- four planes of six each at 66°, plus two birds in individual 83° orbits for polar coverage -- to build a complete low data rate LEO comsat system; Russian launchers will be used throughout. This experimental prototype also carries a small thermal-control experiment for USAF Phillips Lab.


 Program: Faisat-Coscon

Alliance (Oct 1995) of Final Analysis & Polyot Enterprises for global mobile and fixed satellite communications. They intend to manufacture and launch small satellites into low earth orbit. The alliance also intends to market mobile and fixed satellite communications on a global basis with service providers to be selected. The alliance is named FAISAT(TM)-COSCON after the planned commercial satellites of the two companies.

Polyot will be the service provider in Russia and the CIS countries. Final Analysis will provide training in business development, marketing and sales to Polyot for their commercial services.

They will deliver advanced digital data services (non-voice) to include delivery of low-cost applications for SCADA, asset tracking and environmental monitoring, messaging and e-mail.

The first experimental satellite is due early 1996. The launching services will be provided by Polyot: 4 dedicated Cosmos rockets (26 satellites to be launched)

The service is stillto be FCC licensed

Contact

Final Analysis (Greenbelt, Maryland)

Tel: +1-301-474-0111

Fax: +1-301-474-3228

Polyot (Omsk, Russia)

Tel/Fax: +7-3812-579-201


 Firewheel

End of life

Out of service	23 May 1980
Cause	Explosed with Ariane L02

Was operated by Max Plank INST.


 Program: Fleetsatcom

American military geostationary telecommunications satellite program operated by USAF, US Navy and the DoD.

UHF-band (244-400 MHz)

Transponders	23
Mass	1900 kg
Capacity	1300 phone circuits

Can be heard at 268.45 MHz?


Program: Fleetsatcom

Fleetsatcom 1

Fleetsatcom 2

Fleetsatcom 3

Fleetsatcom 4

Fleetsatcom 5

Fleetsatcom 6

Fleetsatcom 7

Fleetsatcom 8


 Fleetsatcom 1

Also called OPS 6391

General

Designation	10669 / 78016A
Launch date	9 Feb 1978
Country of origin	United States
Mission	Military: telecommunications
Geostationary orbit	see below
Launch vehicle	Atlas Centaur
Launch site	Cape Canaveral
Location

Begin	End	Position
L: 9 Feb 1978		100°W
Mar 1995	...	15°W, inclined


 Fleetsatcom 2

Also called OPS 6392

General

Designation	11353 / 79038A
Launch date	4 May 1979
Country of origin	United States
Mission	Military: telecommunications
Geostationary orbit	75°E
Launch vehicle	Atlas Centaur
Launch site	Cape Canaveral
End of life

Out of service	yes


 Fleetsatcom 3

Also called OPS 6393

General

Designation	11669 / 80004A
Launch date	18 Jan 1980
Country of origin	United States
Mission	Military: telecommunications
Geostationary orbit	23°W, inclined
Launch vehicle	Atlas Centaur
Launch site	Cape Canaveral
End of life

Out of service	Sep 1995


 Fleetsatcom 4

Also called OPS 6394

General

Designation	12046 / 80087A
Launch date	31 Oct 1980
Country of origin	United States
Mission	Military: telecommunications
Geostationary orbit	172°E, inclined
Launch vehicle	Atlas Centaur
Launch site	Cape Canaveral


 Fleetsatcom 5

General

Designation	12635 / 81073A
Launch date	6 Aug 1981
Country of origin	United States
Mission	Military: telecommunications
Geostationary orbit
Launch vehicle	Atlas Centaur
Launch site	Cape Canaveral
End of life

Out of service	Aug 1981
Cause	The satellite reached GTO, but imploding payload shroud damaged it


 Fleetsatcom 6

End of life

Out of service	26 Mar 1987
Cause	Launch failure (Atlas Centaur)


 Fleetsatcom 7

Also called USA 020

General

Designation	17181 / 86096A
Launch date	5 Dec 1986
Country of origin	United States
Mission	Military: telecommunications
Geostationary orbit	100°W, inclined
Launch vehicle	Atlas Centaur
Launch site	Cape Canaveral


 Fleetsatcom 8

Also called USA 046

General

Designation	20253 / 89077A
Launch date	25 Sep 1989
Country of origin	United States
Mission	Military: telecommunications
Geostationary orbit	23°W, inclined
Launch vehicle	Atlas Centaur
Launch site	Cape Canaveral


 Program: Foton

Also called Photon

Scientific Russian program


Program: Foton

Foton 01 was Cosmos 1645

Foton 02 was Cosmos 1744

Foton 03 was Cosmos 1841

Foton 08 was in Oct 1992

Foton 09

Foton 10


 Foton 09

General

Designation	23122 / 94033A
Launch date	14 Jun 1994 at 16:00 UT
Country of origin	CIS
Mission	Scientific
Perigee/Apogee	229/385 km
Inclination	62.8°
Period	90.4 min
Launch vehicle	Soyuz
Launch site	Plesetsk
Mass at launch	8200 kg

The spacecraft, with a research payload of 700 kg, is expected to orbit for 18 days, conducting microgravity experiments in solid state and biological disciplines.

End of life

Landing	2 Jul 1994


 Foton 10

General

Designation	23497 / 95006A
Launch date	16 Feb 1995 at 17:40 UT
Country of origin	CIS
Mission	Scientific: microgravity studies
Perigee/Apogee	228/391 km
Inclination	62.8°
Period	94 min
Launch vehicle	Soyuz U
Launch site	Plesetsk LC43
Mass at launch	6300 kg (retrievable experiment: 2250 kg)

The mission carried "KASHTAN", "ZONA", "SPLAV", "Biobox 2", "IBIS" instruments for zero-gravity material, and biotechnological experiments.

Biobox 2 is an incubator with experiments on cells responsible for bone mineralization and on small living organism. These experiments will contribute to a better understanding of the phenomenon of bone mass loss experienced by astronauts in space and will help identify and quantify the influence of absence of gravity on living systems.

End of life

Landing	3 Mar 1995

The descent cabin was severly damaged when it was dropped by the helicopter carrying it back for deintegration. Thus many experiments were destroyed.

Technical data

The Foton recoverable materials processing satellite, built by the Central Specialized Design Bureau in Samara, is based on the Vostok/Zenit spy satellite bus.


 FR 1

General

Designation	01814 / 65101A
Launch date	6 Dec 1965
Country of origin	France
Mission	Scientific: ionosphere study
Perigee/Apogee	696/707 km
Inclination	75.9°
Period	98.8 min
Launch vehicle	Scout #39
Mass at launch	62 kg
End of life

Out of service	28 Feb 1969
Cause	Stopped transmitting


 Freja

In the nordic mythology Freja is the goddess of Love and fecundity

General

Designation	22161 / 92064A
Launch date	6 Oct 1992
Country of origin	Sweden
Operator	Swedish Space Corporation
Mission	Scientific: magnetosphere study
Perigee/Apogee	586/1767 km
Inclination	63°
Period	108.9 min
Launch vehicle	Long March 3
Launch site	Jiuqua
Mass at launch	230 kg

Successor of Viking with instruments for research into the Earth's magnetosphere and the aurora. Carries magnetic particles detectors and magnetic field captors.

Cost: $150 million

Technical data

Specifications

Prime contractor	Swedish Space Corp.
Mass at launch	265 kg
Diameter	2.2 m
Stabilization	Spin stabilized (10 rpm)
DC power	EOL: 130 W
Design lifetime	2 years
Payload

Boom length	15 m
Telemetry data rate	250-500 kbps (2 Mbps burst)
Transmitter power	2 W
Frequencies	400.55 MHz (1200 bps), 2208.163 MHz


 Program: Fuji

Means "glycine flower"

Japanese small telecommunications satellite program


Program: Fuji

Fuji 1A

Fuji 1B


 Fuji 1A

Also called JAS 1A or FO-12 or Oscar 12

General

Designation	16909 / 86061B
Launch date	12 Aug 1986
Country of origin	Japan
Mission	Telecommunications
Perigee/Apogee	1479/1497 km
Inclination	50°
Period	115.7 min
Launch vehicle
Launch site	Tanegashima
End of life

Out of service	fall 1989
Cause	power problems

Launched with Experimental Geodetic Payload - first multi-payload launch by NASDA.

Technical data

Specifications

Mass at launch	50 kg
Stabilization	passive magnetic
DC power	8.5 W (6 Ah NiCd battery)


 Fuji 1B

Also called JAS 1A or FO-20 or Oscar 20

General

Designation	20480 / 90013C
Launch date	7 Feb 1990
Country of origin	Japan
Mission	Telecommunications
Perigee/Apogee	908/1743 km
Inclination	99°
Period	112.2 min
Launch vehicle
Launch site	Tanegashima
Mass at launch	50 kg
End of life

Out of service	yes
Technical data

Packet Radio Mailbox and Digipeater, and a mode J analog transponder.

Mode JD uplink	1200bps Manchester coded (Biphase-L) FSK (FM) AX.25 145.850 145.870 145.890 145.910 MHz
Mode JD downlink	1200bps BPSK (SSB) AX.25 435.910 MHz
Mode JA uplink	145.900 - 146.000 MHz (SSB, CW)
Mode JA downlink	435.900 - 435.800 MHz (SSB, CW, inverting)
Mode JA Beacon	435.795 MHz


 Program: Galaxy

Operated by Hughes Communications Inc (HCI)

Contact

Hughes Communications Inc.

PO Box 92424, Los Angeles, CA 90009, USA

Tel: +1-800-824-8133 / +1-310-607-4000

Fax: +1-310-607-4255


Program: Galaxy

Galaxy 1

Galaxy 1R

Galaxy 1R failure

Galaxy 2

Galaxy 3

Galaxy 3R

Galaxy 4

Galaxy 5

Galaxy 6

Galaxy 7

Galaxy 8I

Galaxy 9

Galaxy 10


Galaxy 1, 2 & 3's specifications

Prime contractor	Hughes
Platform	HS-376
Mass at launch	1200 kg
Mass in orbit	654 kg
Diameter	2.16 m
Height	6.6 m stowed
Stabilization	Spin stabilized
DC power	BOL: 990 W
Design lifetime	10 years


Galaxy 1, 2 & 3's C-band

Main transponders	24
Backup transponders	6
Power	9 W (TWTA)
Bandwidth	36 MHz
Coverage
EIRP	34 dBW
Polarization	linear


Galaxy 4, 7 & 3R's specifications

Prime contractor	Hughes
Platform	HS-601
Mass at launch	2950 kg
Mass in orbit	BOL: 1692 kg EOL: 1320 kg
Dimension	2.27 x 2.27 x 2.27 m
Solar array	24.7 m span
Stabilization	3 axis
DC power	BOL: 6000 W EOL: 4700 W
Design lifetime	15 years


Galaxy 4, 7 & 3R's C-band

Main transponders	24
Backup transponders	6
Power	16 W (SSPA)
Bandwidth	36 MHz
Coverage & EIRP	CONUS: 42 dBW Alaska, Hawaii: 33 dBW
Polarization	linear

Strap-crossing: transponders 18 and 24 can be feed by the Ku-band transponders 17 and 23 respectively


Galaxy 4 & 7's Ku-band

Main transponders	24
Backup transponders	6
Power	50 W (TWTA)
Bandwidth	8 transponders of 54 MHz 16 transponders of 27 MHz
Coverage
EIRP	45 dBW
Polarization	linear

Strap-crossing: transponders 17 and 23 can be feed by the C-band transponders 18 and 24 respectively


Galaxy 1R, 5 & 9's specifications

Prime contractor	Hughes
Platform	HS-376
Mass at launch
Mass in orbit
Diameter	2.16 m
Height	6.6 m stowed
Stabilization	Spin stabilized
DC power	BOL: 990 W
Design lifetime	10 years


Galaxy 1R, 5 & 9's C-band

Main transponders	24
Backup transponders	6
Power	16 W (TWTA)
Bandwidth	36 MHz
Coverage	CONUS, Alaska, Hawaii, Caribbean
EIRP
Polarization	linear


 Galaxy 1

General

Designation	14158 / 83065A
Launch date	28 Jun 1983
Country of origin	United States
Mission	Telecommunications
Geostationary orbit	133°W
Launch vehicle	Thor Delta #170
End of life

Out of service	yes
Technical data

Specifications

C-band

C-band transponder frequency chart


 Galaxy 1R failure

General

Launch date	22 Aug 1992
Country of origin	United States
Mission	Telecommunications
Launch vehicle	Atlas Centaur
Launch site	Cape Canaveral
End of life

Out of service	23 Aug 1992
Cause	Fail to orbit because the launcher's 3rd stage malfunctioned

Was an HS-376


 Galaxy 1R

General

Designation	23016 / 94013A
Launch date	19 Feb 1994
Country of origin	United States
Mission	Telecommunications
Geostationary orbit	133°W
Launch vehicle	Delta 2 #225

The launch was aborted on 9 Feb 1994 during main engine ignition and the vehicle did not leave the pad.

Technical data

Specifications

C-band

C-band transponder frequency chart

EIRP coverage (dBW)

C-band Horizontal

C-band Vertical


Galaxy 1R's EIRP (C-band Horizontal)


Galaxy 1R's EIRP (C-band Vertical)


 Galaxy 2

General

Designation	14365 / 83098A
Launch date	22 Sep 1983
Country of origin	United States
Mission	Telecommunications
Geostationary orbit	74°W
Launch vehicle	Thor Delta #173
End of life

Out of service	yes
Technical data

Specifications

C-band

C-band transponder frequency chart


 Galaxy 3

General

Designation	15308 / 84101A
Launch date	21 Sep 1984
Country of origin	United States
Mission	Telecommunications
Geostationary orbit	93.5°W
Launch vehicle	Thor Delta #176
End of life

Out of service	Oct 1995
Cause	was deorbited
Technical data

Specifications

C-band

C-band transponder frequency chart


 Galaxy 3R

General

Designation	23741 / 95069A
Launch date	15 Dec 1995
Country of origin	United States
Mission	Telecommunications
Geostationary orbit	95°W
Launch vehicle	Atlas 2A #97
Mass at launch	3380 kg

Cost: $150 million

Using a combination of digital compression and tightly focused spot beams, Galaxy 3R will use 24 Ku-band transponders to deliver as many as 144 channels of digital video and 60 channels of CD- quality audio via 24-inch (60 cm) dishes. The service is called Galaxy Latin America (tm) and operated by this company.

In 1998 Galaxy 8I will transmit the DIRECTV Latin America programming, subject to FCC approval.

Technical data

Specifications

C-band

C-band transponder frequency chart

Ku-band transponder frequency chart

EIRP coverage (dBW)

C-band Horizontal

C-band Vertical

Ku-band

Main transponders	24
Backup transponders	6
Power	50 or 63? W (TWTA)
Bandwidth	16 transponders of 27 MHz 8 transponders of 54 MHz
Coverage	2 beams (12 transponders each): Latin America and Brazil
EIRP	49 dBW
Polarization	circular

Strap-crossing: transponders 17 and 23 can be feed by the C-band transponders 18 and 24 respectively


Galaxy 3R's EIRP (C-band Horizontal)


Galaxy 3R's EIRP (C-band Vertical)


 Galaxy 4

General

Designation	22694 / 93039A
Launch date	25 Jun 1993
Country of origin	United States
Mission	Telecommunications
Geostationary orbit	99°W
Launch vehicle	Ariane V57
Technical data

Specifications

C-band

Ku-band

C-band transponder frequency chart

Ku-band transponder frequency chart

EIRP coverage (dBW)

C-band Horizontal

C-band Vertical

Ku-band Horizontal

Ku-band Vertical

Launched using the PVA (Perigee Velocity Augmentation) technic. The transfert orbit is 200/27975 km and then the apogee is upped to 35975 km with the satellite's kick motor and then gradually circularized.

Vertically polarized transponders are theoretically the only transponders that can be made into half transponders. Cross-strapping: C-band transponders 18 and 24 can cross-strap to Ku-band transponders 17 and 23.


Galaxy 4's EIRP (C-band Horizontal)


Galaxy 4's EIRP (C-band Vertical)


Galaxy 4's EIRP (Ku-band Horizontal)


Galaxy 4's EIRP (Ku-band Vertical)


 Galaxy 5

General

Designation	21906 / 92013A
Launch date	14 Mar 1992
Country of origin	United States
Mission	Telecommunications
Geostationary orbit	125°W
Launch vehicle	Atlas Centaur
Launch site	Cape Canaveral
Technical data

Specifications

C-band

C-band transponder frequency chart

EIRP coverage (dBW)

C-band Horizontal

C-band Vertical


Galaxy 5's EIRP (C-band Horizontal)


Galaxy 5's EIRP (C-band Vertical)


 Galaxy 6

General

Designation	20873 / 90091B
Launch date	12 Oct 1990
Country of origin	United States
Mission	Telecommunications
Geostationary orbit	see below
Launch vehicle	Ariane V39

This satellite is Westar 6S (Westar 6's backup satellite) modified.

Location

Begin	End	Position
L: 12 Oct 1990		93°W
< May 1992	May 1992 >	99°W
< Oct 1993	early 1994	103°W
spring 1994		74°W
Technical data

EIRP coverage (dBW)

Horizontal

Vertical

Specifications

Prime contractor	Hughes
Platform	HS-376
Mass at launch	1212 kg
Mass in orbit	708 kg
Diameter	2.16 m
Height	6.6 m stowed
Stabilization	Spin stabilized
DC power	990 W
Design lifetime	10 years
C-band

Main transponders	24
Backup transponders	6
Power	10.2 W (TWTA)
Bandwidth	36 MHz
Coverage	CONUS, Alaska, Hawaii, Caribbean
EIRP max	39 dBW
Polarization	linear

C-band transponder frequency chart


Galaxy 6's EIRP (C-band Horizontal)


Galaxy 6's EIRP (C-band Vertical)


 Galaxy 7

General

Designation	22205 / 92072A
Launch date	28 Oct 1992
Country of origin	United States
Mission	Telecommunications
Geostationary orbit	91°W
Launch vehicle	Ariane V54
Technical data

Specifications

C-band

Ku-band

C-band transponder frequency chart

Ku-band transponder frequency chart

EIRP coverage (dBW)

C-band Horizontal

C-band Vertical

Ku-band Horizontal

Ku-band Vertical

The spacecraft was launched using the PVA (Perigee Velocity Augmentation) technic. The transfert orbit was 200/27975 km and then the apogee was upped to 35975 km with the satellite's kick motor and then gradually circularized.

Vertically polarized transponders are theoretically the only transponders that can be made into half transponders. Cross-strapping: C-band transponders 18 and 24 can cross-strap to Ku-band transponders 17 and 23.


Galaxy Ku-band frequency chart
 Ku-band transponder frequency chart (GHz)

Horizontal Uplink	Horizontal Downlink	Transponder	Vertical Downlink	Vertical Uplink
14.020		1	11.720
	11.750	2		14.050
14.050		3	11.750
14.080		4	11.780
	11.810	5		14.110
14.110		6	11.810
14.140		7	11.840
	11.870	8		14.170
14.170		9	11.870
14.200		10	11.900
	11.930	11		14.230
14.230		12	11.930
14.260		13	11.960
	11.990	14		14.290
14.290		15	11.990
14.320		16	12.020
	12.050	17		14.350
14.350		18	12.050
14.380		19	12.080
	12.110	20		14.410
14.410		21	12.110
14.440		22	12.140
	12.170	23		14.470
14.470		24	12.170


Galaxy 7's EIRP (C-band Horizontal)


Galaxy 7's EIRP (C-band Vertical)


Galaxy 7's EIRP (Ku-band Horizontal)


Galaxy 7's EIRP (Ku-band Vertical)


 Galaxy 8I

I stands for International, to serve Mexico, the Carribbean, and South and Central America

This satellite should replace Galaxy 3R in 1998. It's antennas will cover a larger area than the Galaxy 3R satellite, especially over the Caribbean and Central America.

Based on an HS-601 with ~5000 W power


 Galaxy 9

General

Designation
Launch date	planned in April 1996
Country of origin	United States
Mission	Telecommunications
Geostationary orbit	123°W
Launch vehicle	Delta 2 7925
Launch site	Cape Canaveral

Should move to 129°W after Galaxy 10 is launched

Technical data

Specifications

C-band

C-band transponder frequency chart


 Galaxy 10

Will be the first HS 702 satellite launched in 1998-99 to replace SBS 5 at 123°W

C- and Ku-band satellite

Specifications

Prime contractor	Hughes
Platform	HS 702
Mass at launch
Mass in orbit
Dimension
Solar array	11000 W (gallium arsenide solar cells)
Stabilization	3 axis
DC power
Design lifetime
Station keeping	Xenon Ion Propulsion System (XIPS)


 Program: Gals

Soviet direct TV built satellites. The satellites have been bought by the Land Group, a Chinese non-state sector company

Intersputnik has plans to operate Gals R12 satellites from 1997 on.


Program: Gals

Gals 1

Gals 2


Specifications

Prime contractor	Informcosmos
Platform	NPO Gals
Mass at launch	2500 kg
Mass in orbit
Diameter	2.5 m
Solar array	twin panels
Stabilization	3 axis
DC power	2400 W
Design lifetime	5 to 7 years


Ku-band

Main transponders	3
Backup transponders
Power	150-300 W (TWTA)
Bandwidth	27 MHz
Coverage	2 spot beams (steerable): A: 2.5° x 1.25° (2 transponders) B: 1.2° x 0.9° (1 transponder)
EIRP	57 dBW
Polarization	circular
Frequencies	uplink: 17404.2 - 17883.7 MHz downlink: 11804.2 - 12283.7 MHz

Receive antenna: spot: 2° x 2°


 Gals 1

General

Designation	22963 / 94002A
Launch date	20 Jan 1994
Country of origin	CIS
Mission	Telecommunications
Geostationary orbit	71°E
Launch vehicle	Proton #219
Technical data

Specifications

Ku-band


 Gals 2

General

Designation	23717 / 95063A
Launch date	17 Nov 1995 at 14:30 UT
Country of origin	CIS
Mission	Telecommunications
Geostationary orbit	71°E
Launch vehicle	Proton #237

Land has leased the satellite for $9 million a year to Global DBS Company, whose shareholders include the Loral Corp, General Instruments Co and TCI Cable TV Co, all of the United States, and British General Telecommunications Ltd/Asian TV network.

Technical data

Specifications

Ku-band


 Gals 3

for 1997


 Gals 4

for 1998


 Gamma

General

Designation	20683 / 90058A
Launch date	11 Jul 1990
Country of origin	CIS
Mission	Scientific: gamma-ray astronomy
Perigee/Apogee	382/387 km
Inclination	51.6°
Period	92.3 min
Launch vehicle
Launch site	Tyuratam
End of life

Decay	28 Feb 1992


 Program: GE

Telecommunication program operated by GE Americon

GE 5, 6 & 7 should be expansion satellites launched in 1998-2000

Another project of GE Americom: a set of satellite for global services; operated from Gibraltar. Planned orbital locations include 3°E, 6.5°W, 10°W, 15°W and 23°W for Europe; 37.5°E, 47°E and 51°E for Africa; and 97°E, 100.7°E, 105.3°E and 108.2°E for Asia and the Pacific. The proposed satellites would be used mainly for video programming distribution, including direct-to-home, cable headend and other broadcast applications. The planned spacecraft design would accommodate both analog and digital video formats, as well as other uses including VSAT and data networks.

Contact

GE Americom

4 Research Way, Princeton, NJ 08540, USA

Tel: +1-609-987-4200

Fax: +1-609-987-4495

NYSE: GE


Program: GE

GE 1

GE 2

GE 3

GE 4


GE's specifications

Prime contractor	Lockheed Martin Astro Space
Platform	A2100
Mass at launch	2250 kg
Mass in orbit
Dimension
Solar array
Stabilization
DC power
Design lifetime	15 years


GE's C-band

Main transponders	24
Backup transponders
Power	20 W
Bandwidth	36 MHz
Coverage
EIRP
Polarization


GE's Ku-band

Main transponders	24
Backup transponders
Power	60 W
Bandwidth	36 MHz
Coverage
EIRP	49 dBW
Polarization


 GE 1

General

Designation
Launch date	early 1996
Country of origin	United States
Mission	Telecommunications
Geostationary orbit	103°W
Launch vehicle	Ariane
Launch site

Gstar 1 replacement

Technical data

Specifications

C-band

Ku-band


 GE 2

General

Designation
Launch date	planned late-1996
Country of origin	United States
Mission	Telecommunications
Geostationary orbit	85°W
Launch vehicle	Atlas 2A (AC 123)
Launch site

Satcom K1 replacement. All the Ku-band transponders have been secured for 4 years (with an option up to 15 years) by Primestar

Technical data

Specifications

C-band

Ku-band


 GE 3

could be launched to 127°W, Gstar 2 replacement


 GE 4

should replace Spacenet 3R in the last quarter on 1999


 Program: GE*Star

Geostationary communication program operated by GE American Communications, Inc., a GE Capital Services company

The planned system should use Ka-band to provide broadband, high-speed digital communications connecting the United States, North America, Europe, Asia, India, the Pacific, the Caribbean, South America and Central America, as well as providing services within those regions.

The system would feature 9 satellites providing each 1000 MHz bandwith. The spacecraft will feature on-board processors that can accommodate large streams of data traffic and switch them between spot beams to provide full connectivity and worldwide coverage.

Proposed locations: 106°W, 82°W, 16°E, 38°E and 108°E

Contact

GE Americom

4 Research Way, Princeton, NJ 08540, USA

Tel: +1-609-987-4200

Fax: +1-609-987-4495

NYSE: GE


 Program: Geizer

Russian military telecommunication program. The satellites composing this program are part of the Cosmos fleet. Those geostationary satellites are located on the 'Potok' slots. Potok was a telecommunication project designed in the early 80ies; was to operate in C-band. Three slots were registered with the ITU as Potok: 13.5°W, 80°E and 168°E.

Some satellites could have been leased as standard telecommunication satellites to transmit phone traffic.


Program: Geizer

Cosmos 1366

Cosmos 1540

Cosmos 1738

Cosmos 1888

Cosmos 1961

Cosmos 2085

Cosmos 2172

Cosmos 2291

Cosmos 2319


Geizer's specifications

Prime contractor	NPO-PM
Platform	Geizer
Mass at launch
Mass in orbit
Dimension
Solar array
Stabilization
DC power
Design lifetime	probably 3 to 5 years


 Gemstar

Global Messaging Satellite, also called Vitasat

General

Launch date	15 Aug 1995
Country of origin	United States
Operator	Volunteers In Technical Assistance organization (VITA) based in Arlington, Virginia
Mission	Telecommunications
Launch vehicle	LLV 01
Mass at launch	150 kg
End of life

Out of service	15 Aug 1995
Cause	Launch failure

Cost: between $2 million and $3 million, built by CTA Inc of Rockville, Md (base on the Gemstar bus).

Was designed to provide electronic mail services and global location services for trucking fleet operators.


 GEO-IK

General

Designation	23411 / 94078A
Launch date	24 Nov 1994 at 02:54 UT
Country of origin	CIS
Mission	Scientific: geodetic survey (Musson bus)
Perigee/Apogee	1480/1526 km
Inclination	73.6°
Period	116 min
Launch vehicle	Cyclone 3
Launch site	Plesetsk LC32

It also carried an experimental Elekon positioning equipment to monitor movements of land and sea transportations, to optimize and increase efficiency.

The satellite is gravity-gradient stabilized.


 Geos 3

General

Designation	07734 / 75027A
Launch date	9 Apr 1975
Country of origin	United States
Mission	Scientific: geodesy
Perigee/Apogee	820/845 km
Inclination	115°
Period	101.6 min
Launch vehicle	Thor Delta #109
Mass at launch	241 kg

Mission: Ocean and islands map-making.


 Geosat

Also called Geosat Follow-on (GFO)

Operated by Ball Corporation

This will be the second launch of Taurus, planned to be conducted from Vandenberg Air Force Base, California in the Fall of 1996.

For the GFO mission, Taurus will use Thiokol's Castor 120 solid rocket motor as the vehicle's first stage, and incorporate a larger, Orbital-developed payload fairing, providing a 120% increase in payload volume.  The GFO mission will be the first to follow the highly- successful maiden flight of Taurus carried out in March 1994.

Modifications to the Taurus booster, particularly a new payload fairing twice the size of the one used on the first flight, will result in a much more capable rocket. This configuration was proposed for NASA's MedLite program, and another that results in an extra 500 pounds of secondary payload capability for the GFO mission.

GFO represents one of the earliest applications of small satellite technology for operational military missions. Using an advanced radar altimeter, the GFO satellite is designed to provide precise information on changes in sea surface heights, eddies and warm/cold water fronts.  The data will be used to support Navy tactical operations. The GFO contract was awarded to Ball Aerospace Systems Group in August 1992 by the U.S. Navy's Space and Naval Warfare systems command. The Navy contract calls for a "turnkey" satellite system, and contract options for two additional spacecraft. GFO will follow the successful GEOSAT satellite that completed service in January 1990.


 Geotail

General

Designation	22049 / 92044A
Launch date	24 Jul 1992 at 14:26 UT
Country of origin	United States and Japan
Mission	Scientific: lunar gravity study
Perigee/Apogee	41363/58542 km
Inclination	22.4°
Period	4750.6 min
Launch vehicle	Delta 2 #212

Launched under the MELVS contract


 GFZ 1

General

Designation	23558 / 86017JE
Launch date	19 Apr 1995 at 19:12 UT
Country of origin	Germany
Operator	GeoForschungsZentrum Postdam, Germany
Mission	Scientific: geodesy
Perigee/Apogee	383/394 km
Inclination	51.6°
Period	92.3 min
Launch vehicle	n/a
Launch site	Mir

A fake replica was launched on 17 Apr 1995 (catnr: 23557).

25 observatories all over the world will execute measurements by laserreflections. Stations are among others: London, Grasse (France), Postdam, Easterisland, Graz (Austria) and even one in Kirgizie. The stations can 'catch' GFZ 1 with a beamwidth of 200 meters.

Technical data

Specifications

Prime contractor	Kayser-Threde
Platform
Mass at launch	20 kg
Diameter	21 cm
Width
Height
Stabilization
DC power
Design lifetime

Sphere covered with laser retroreflectors


 Program: GGSE

Gravity Gradient Stabilization Experiment

American scientific program


Program: GGSE

GGSE 1

GGSE 2

GGSE 3

GGSE 4

GGSE 5


 GGSE 1

General

Designation	00728 / 64001B
Launch date	11 Jan 1964
Country of origin	United States
Mission	Scientific
Perigee/Apogee	899/916 km
Inclination	69.9°
Period	103.2 min
Launch vehicle	Thor Agena
Launch site	Vandenberg


 GGSE 2

General

Designation	01244 / 65016B
Launch date	9 Mar 1965
Country of origin	United States
Mission	Scientific: geodesy
Perigee/Apogee	896/928 km
Inclination	70.1°
Period	103.2 min
Launch vehicle	Thor Agena
Launch site	Vandenberg


 GGSE 3

General

Designation	01292 / 65016C
Launch date	9 Mar 1965
Country of origin	United States
Mission	Scientific: geodesy
Perigee/Apogee	896/915 km
Inclination	70.1°
Period	103.0 min
Launch vehicle	Thor Agena D
Launch site	Vandenberg


 GGSE 4

General

Designation	02828 / 67053C
Launch date	31 May 1967
Country of origin	United States
Mission	Scientific: geodesy
Perigee/Apogee	903/910 km
Inclination	70.0°
Period	103.1 min
Launch vehicle	Thor Agena D
Launch site	Vandenberg


 GGSE 5

General

Designation	02834 / 67053D
Launch date	31 May 1967
Country of origin	United States
Mission	Scientific: geodesy
Perigee/Apogee	906/913 km
Inclination	70.0°
Period	103.2 min
Launch vehicle	Thor Agena D
Launch site	Vandenberg


 Program: Globalstar

Globalstar is a low-earth orbit (LEO) satellite-based telecommunications system founded by Loral Corp. and Qualcomm Inc. that will offer low-cost, high-quality global telephony and other digital telecommunications services to areas currently underserved or not served by existing wireline and cellular telecommunications systems. Operated by Loral Qualcom Satellite Services Inc.

The satellites will be launched into eight orbital planes, with six satellites in each plane to provide continuous global coverage. Commercial service is anticipated early in 1998.

Space Systems/Loral has a fixed-price contract for the construction of Globalstar's satellites, which it will perform in conjunction with various other members of the international Space Systems/Alliance, which includes Aerospatiale and Alcatel of France, Daimler-Benz Aerospace of Germany and Finmeccanica of Italy, and with Hyundai of South Korea.

Launches

The launch of the first 4 Globalstar satellites is planned for 1997 from Cape Canaveral, aboard a two-stage Delta 2 rocket. McDonnell Douglas Corp. has been awarded a contract valued at about $50 million for the inaugural launch of the Globalstar telecommunications system. The contract also provides for optional additional launches. (An additional eight to 12 Globalstar satellites will be launched by the end of the fourth quarter of 1997.)

3 launches carring each 12 satellites will be conducted from Tyuratam in 1998. The 12-satellite launch configuration will be composed of three tiers of four satellites each, allowing each satellite to be dispensed sequentially. The dispensing technology will be derived from previous Multiple Independent Reentry Vehicle (MIRV) development.

A Long March 2E/TS is to launch 12 satellites in 1998 with new kick stage/solid-propellant deployment system.

Overview

Orbit type	LEO
Orbit range	1389 km
Nb of satellites	48 + 8 backup
Nb of planes	8
Inclination	52°
Nb beams per satellite	16
Coverage	5796 km²
Modulation	CDMA
Mobile uplink freq.	S-Band: 2483.5 - 2500 MHz
Satellite mass	420 kg
Coverage	Worldwide except the poles
Operational date	1998 (planned)
Specifications

Prime contractor	Space Systems/Loral
Platform	Globalstar?
Mass at launch	500 kg
Mass in orbit
Dimension
Solar array
Stabilization	3 axis (orbit determination with GPS)
DC power	1200 W EOL: 1100 W
Design lifetime	8 years
Payload

Capacity	2800 phone circuits
Voice	9600 bps
Fax	yes
Data	9600 bps
Mobile downlink	1610 - 1626.5 MHz via 61-element phased-array antenna
Mobile uplink	2483.5 - 2500 MHz via 91-element phase-array antenna

Compatible with GSM, CDMA and AMPS.


 Program: Glonass

Global'naya Navigatsionnaya Sputnikovaya Sistema

Russian navigation program part of the Cosmos constellation. The satellites carry an atomic clock.

Planes and slots

The Glonass series orbit in three distinct planes that are 120 deg apart. Each plane has eight "slots".

Slot	Plane 1	Plane 2	Plane 3
1	771 (Cosmos 2179)
2	757 (Cosmos 2235)
3	763 (Cosmos 2294)
4	762 (Cosmos 2296)
5	249 (Cosmos 2111)
6	764 (Cosmos 2295)
7	759 (Cosmos 2236)
8	769 (Cosmos 2178)
9
10		781 (Cosmos 2317)
11		785 (Cosmos 2318)
12		767 (Cosmos 2287)
13
14		770 (Cosmos 2288)
15		780 (Cosmos 2316)
16		775 (Cosmos 2289)
17			760 (Cosmos 2275)
18			758 (Cosmos 2277)
19			777 (Cosmos 2309)
20			765 (Cosmos 2307)
21			756 (Cosmos 2205)
22			766 (Cosmos 2308)
23			761 (Cosmos 2276)
24			774 (Cosmos 2204)
Contact

http://www.rssi.ru/SFCSIC/SFCSIC_main.html

Technical data

Frequency (MHz)	L1 = 1602 + 0.5625 * channel L2 = 1246 + 0.4375 * channel


 Program: GMS

Geostationary Meteorological Satellite, also called Himawari which means "sunflower"

Japanese Meteorology Agency satellite program

Originated as Japan's contribution to the international GARP and WWW programs. The satellites are designed to observe cloud cover, land and sea surface and cloud-top temperature, image acquisition, distribution of image data and other met info, collection and relay of weather data from data collection platforms (DCPs) - land, sea and airborne.

Contact

Ministry of Transport

2-1-3 Kasumigaseki, Chiyoda-ku, Tokyo

Tel: +81-03-3212-8341


Program: GMS

GMS 1

GMS 2

GMS 3

GMS 4

GMS 5


GMS's specifications

Prime contractor	Hughes/NEC
Platform	HS 378
Mass at launch	682 kg
Diameter	2.15 m
Height	3.45 m
Stabilization	Spin stabilized
DC power	291 W
Design lifetime	5 years


GMS's payload

VISSR (Visible and IR Spin Scan Radiometer)

Wavebands	0.5-0.75 µm (visible) 10.5-12.5 µm (IR)
Resolution	visible: 1.25 km IR: 5 km
Image repeat frequency	30 minutes (full Earth)
SEM (Space Environment Monitor)

Solar particle flux measurement; XRS (Solar X-ray Sensor); ion chamber sensitive in 2 bands; EPS (Energetic Particle Sensor); detector groups for electron, proton and alpha particle flux.

Communications instruments

WEFAX (Weather Facsimile)

DCS (Data Collection System)


 GMS 1

Also called Himawari 1

General

Designation	10143 / 77065A
Launch date	14 Jul 1977
Country of origin	Japan
Mission	Meteorology
Geostationary orbit	140°E
Launch vehicle	Thor Delta #132
End of life

Out of service	yes
Technical data

Specifications

Payload


 GMS 2

Also called Himawari 2

General

Designation	12677 / 81076A
Launch date	10 Aug 1981
Country of origin	Japan
Mission	Meteorology
Geostationary orbit	140°E
Launch vehicle	N2
Launch site	Tanegashima
End of life

Out of service	yes
Technical data

Specifications

Payload


 GMS 3

Also called Himawari 3

General

Designation	15152 / 84080A
Launch date	2 Aug 1984
Country of origin	Japan
Mission	Meteorology
Geostationary orbit	see below
Launch vehicle	N2
Launch site	Tanegashima
Location

Begin	End	Position
L: 2 Aug 1984		140°E
Feb 1995	Jun 1995	120°E
End of life

Out of service	Jul 1995
Technical data

Specifications

Payload

Downlink frequency-bands: UHF or VHF, L and S-band


 GMS 4

Also called Himawari 4

General

Designation	20217 / 89070A
Launch date	5 Sep 1989
Country of origin	Japan
Mission	Meteorology
Geostationary orbit	see below
Launch vehicle	H1
Launch site	Tanegashima
Location

Begin	End	Position
L: 5 Sep 1989	mid-Jun 1995	140°E
Aug 1995		120°E, inclined
Technical data

Specifications

Payload

Downlink frequency-bands: UHF or VHF, L and S-band


 GMS 5

Also called Himawari 5

General

Designation	23522 / 95011B
Launch date	17 Mar 1995
Country of origin	Japan
Mission	Meteorology
Geostationary orbit	140°E, inclined
Launch vehicle	H2 02

Tested in 159.5°E

Technical data

Specifications

Payload

The spacecraft spins at 100 rpm. It carries a Star 27 solid motor which placed it in geostationary orbit.

The satellite can produce a new image of the Earth every 25 minutes(resolution of 1.25 km (visible) and 5.0 km (infrared)). GMS-5 carries an extra infrared channel to measure atmospheric water-vapour distribution.

Downlink frequency-bands: UHF or VHF, L and S-band


 Program: Goes

Geostationary Operational Environmental Satellite

American program developed for GARP (Global Atmospheric Research Program) and operated by NOAA


Program: Goes

Goes 1

Goes 2

Goes 3

Goes 4

Goes 5

Goes 6

Goes G

Goes 7

Goes 8

Goes 9


Goes 6 & 7's specifications

Prime contractor	Hughes
Mass at launch	835 kg
Length	2.16 m
Height	3.53 m
Stabilization	Spin stabilized
Design lifetime	5 years


Goes 6 & 7's payload

VAS (VISSR (Visible and IR Spin Scan Radiometer) Atmospheric Sounder)

Wavebands	0.55-075 µm (visible): 8 channels 3.7-7.3 µm (near IR): 2 channels 7.7-14.7 µm (mid IR): 2 channels 6.7-14.7 µm (mid IR): 2 channels
Resolution	visible: 1, 2, 4 and 8 km IR: 8-14 km
Image repeat frequency	full Earth: 30 minutes sectors: 3 minutes

Also equipped with 12 IR channels in a detector array for measurement of 3D structure of atmospheric temperature and water vapor distribution.

SEM (Space Environment Monitor)

Measures solar particule flux: XRS (Solar X-ray Sensor); ion chamber sensitive in 2 bands; EPS (Energetic Particle Sensor); 3 detector groups for electron, proton and alpha particle flux.

Communications instruments

WEFAX (Weather Facsimile)

DCS (Data Collection System)


Goes 8, 9 and 10's specifications (Goes Next)

Prime contractor	Space Systems/Loral
Mass at launch	2300 kg
Stabilization	3 axis
Design lifetime	5 years


Goes 8, 9 and 10's payload (Goes Next)

Imager (5-channel imaging radiometer)

Wavebands	3.7, 6.7, 10.7, 12µ: visible, IR
Resolution	visible: 1 km IR: 4 km
Sounder (vertical sounder)

Wavebands	visible: 1 channel IR: 18 channels
Resolution	visible: 1 km IR: 2 km
SEM (Space Environment Monitor)

XRS (Solar X-ray Sensor): ion chamber sensitive in 2 bands

EPS (Energetic Particle Sensor): 3 detector groups for electron, proton and alpha particle flux

Communications instruments

WEFAX (Weather Facsimile)

DCS (Data Collection System)

Also equipped with SXI (Solar X-ray Imager) and a Sarsat repeter.


 Goes 1

Also called SMS 3 or Goes A

3rd satellite of the SMS series and first operational satellite operated by the NOAA

General

Designation	08366 / 75100A
Launch date	16 Oct 1975
Country of origin	United States
Mission	Meteorology
Geostationary orbit	see below
Launch vehicle	Thor Delta #116
Mass at launch	627 kg (294 kg?)

Visible and IR photos

Location

Begin	End	Position
L: 16 Oct 1975		60°E
		90°W
		115°W
		135°W
29 Jun 1991		81.2°W; inclination: 10.5°
End of life

Out of service	yes
Technical data

Built by Ford Aerospace

Transmits on 136.38 MHz


 Goes 2

Also called Goes B

General

Designation	10061 / 77048A
Launch date	16 Jun 1977
Country of origin	United States
Mission	Meteorology
Geostationary orbit	see below
Launch vehicle	Thor Delta #131

The satellite has been reactivated in 1995 to transmit educational programming in S-band. Used by the NSF to transmit live television broadcasts from its South Pole Station to public broadcasting facilities in the United States.

Location

Begin	End	Position
L: 16 Oct 1975		105°W
24 Oct 1993		136°W, inclination: 9.4°
?		see the Clarke Belt chart for latest location
Technical data

Built by Ford Aerospace

Downlink frequency: 136.38, 1691 and 2297.5925 MHz


 Goes 3

Also called Goes C

General

Designation	10953 / 78062A
Launch date	16 Jun 1978
Country of origin	United States
Mission	Meteorology
Geostationary orbit	see below
Launch vehicle	Thor Delta #142

The satellite has been reactivated in 1995 to transmit educational programming in S-band. Used by the University of Hawaii to transmit educational programming throughout the Hawaiian Islands.

Location

Begin	End	Position
L: 16 Jun 1978		60°E
24 Oct 1993		176.2°W, inclination: 8°
~Jan 1995	Jan 1996	drifting East
Feb 1996		103°W, inclination: 11°
End of life

Out of service	probably
Technical data

Built by Ford Aerospace

Downlink frequency: 136.38, 1691 and 2297.5925 MHz


 Goes 4

Also called Goes D

General

Designation	11964 / 80074A
Launch date	9 Sep 1980
Country of origin	United States
Mission	Meteorology
Geostationary orbit	135°W
Launch vehicle	Thor Delta #152
End of life

Out of service	yes
Technical data

Built by Hughes


 Goes 5

Also called Goes E

General

Designation	12472 / 81049A
Launch date	22 May 1981
Country of origin	United States
Mission	Meteorology
Geostationary orbit	see below
Launch vehicle	Thor Delta #154
Mass at launch	900 kg
Location

Begin	End	Position
L: 22 May 1981		75°W
End of life

Out of service	probably
Technical data

Built by Hughes


 Goes 6

Also called Goes F

General

Designation	14050 / 83041A
Launch date	28 Apr 1983
Country of origin	United States
Mission	Meteorology
Geostationary orbit	see below
Launch vehicle	Thor Delta #168

Mission: high altitude windspeed and direction monitoring (via cloud movement); high altitude cloud top detectin (electrical storms, tornadoes); sea surface temperature mapping, etc. Image acquisition, distribution of image data and other met info, collection and relay of weather data from data collection platforms (DCPs) - land, sea, airborne.

Location

Begin	End	Position
L: 28 Apr 1983		135°W
1984		100°W
		110°W
1989	1989	135°W
End of life

Out of service	21 Jan 1989
Cause	Failure
Technical data

Specifications

Payload


 Goes G

General

Launch date	3 May 1986
Country of origin	United States
Mission	Meteorology
Launch vehicle	Thor Delta #178
End of life

Out of service	3 May 1986
Cause	Launch failure
Technical data

Specifications

Payload


 Goes 7

Also called Goes H

General

Designation	17561 / 87022A
Launch date	26 Feb 1987
Country of origin	United States
Mission	Meteorology
Geostationary orbit	see below
Launch vehicle	Thor Delta #180

Mission: high altitude windspeed and direction monitoring (via cloud movement); high altitude cloud top detectin (electrical storms, tornadoes); sea surface temperature mapping, etc. Image acquisition, distribution of image data and other met info, collection and relay of weather data from data collection platforms (DCPs) - land, sea, airborne.

Location

Begin	End	Position
L: 26 Feb 1987	1989	79.5°W
1989	?	98°W
Feb 1995	...	136°W
Technical data

Specifications

Payload

Transmits in VHF-, L- and S-band. It is equipped with a Sarsat repeter


 Goes 8

Also known as Goes I

General

Designation	23051 / 94022A
Launch date	13 Apr 1994
Country of origin	United States
Mission	Meteorology
Geostationary orbit	75°W
Launch vehicle	Atlas Centaur

On board were instruments for high resolution visible and UV imagers, and "sounders" for temperature and moisture profiles. Also on board were energetic particle detectors and a magnetometer.

Technical data

Specifications

Payload

Transmits in VHF-, L- and S-band


 Goes 9

Also known as Goes J

General

Designation	23581 / 95025A
Launch date	23 May 1995
Country of origin	United States
Mission	Meteorology
Geostationary orbit	90.5°W
Launch vehicle	Atlas Centaur

Is to replace Goes 7

Cost: $220 million

Technical data

Specifications

Payload

Transmits in VHF-, L- and S-band


 Program: Gorizont

The Gorizont satellite system is a general purpose network for communications owned by Informcosmos and operated by Intersputnik. The network is composed of 370 ground stations.

The payloads are Statsionar (C-band) and Loutch (Ku-band).


Program: Gorizont

Gorizont 01 Gorizont 02 Gorizont 03 Gorizont 04 Gorizont 05 Gorizont 06 Gorizont 07 Gorizont 08 Gorizont 09 Gorizont 10 Gorizont 11 Gorizont 12 Gorizont 13 Gorizont 14 Gorizont 15	Gorizont 16 Gorizont 17 Gorizont 18 Gorizont 19 Gorizont 20 Gorizont 21 Gorizont 22 Gorizont 23 Gorizont 24 Gorizont 25 Gorizont 26 Gorizont 27 Gorizont 28 Gorizont 29 Gorizont 30	Gorizont 31


Gorizont's specifications

Prime contractor	NPO PM
Platform	NPO Gorizont
Mass at launch	2120 kg
Diameter	about 2 m
Height	about 5 m
Stabilization	3 axis
DC power	1300 W
Design lifetime	3 to 5 years

No North-South stabilisation. They also are equipped with one X- or L-band transponder.


Antenna Specifications

Antenna	Frequency band	Function / max gain	Coverage	Beam width	Steerability
					North/South	West/East
A1	C	TX / 19.0	global	17°x17°	none	none
A2	C	RX / 19.0	global	17°x17°	none	none
A3	C	TX / 30.0	spot	5°x5°	none	once West to East or East to West
A4	C	TX / 22.0	hemi	9°x18°	none	none
A5	C	RX / 19.0	global	17°x17°	none	none
A6	C	TX / 19.0	global	17°x17°	none	none
A7	C	RX / 25.0	elliptical	6°x12°	none	none
A8	C	TX / 25.0	elliptical	6°x12°	none	none
A9	Ku	RX and TX / 30.0	spot	5°x5°	none	once East to East or East to West

See also the transponder/antenna connection diagram


Gorizont's C-band

Main transponders	6
Backup transponders
Power	1 transponder (#6) of 40 W (TWTA) 5 transponders of 15 W (TWTA)
Bandwidth	spot (#6): 40 MHz others: 36 MHz
Coverage and EIRP	transponder #6: global beam (A1): 35.6 dBW spot beam (A3): 46.1 dBW 1 global beam(A6): 28.5 dBW 1 large hemispheric beam (A4): 31 dBW 1 little hemispheric beam (A8): 34 dBW
Polarization	uplink: LHCP downlink: RHCP


Gorizont's Ku-band

Main transponders	1
Backup transponders
Power	20 W (TWTA)
Bandwidth	36 MHz
Coverage & EIRP	spot: 39.2 dBW
Polarization	uplink: LHCP downlink: RHCP


Gorizont's transponder frequency chart (GHz)

LHCP Uplink	LHCP Downlink	Transponder	RHCP Downlink	RHCP Uplink
6.000		6	3.675
6.050		7	3.725
6.100		8	3.775
6.150		9	3.825
6.200		10	3.875
6.250		11	3.925
	11.525	K1		14325


Gorizont transponder/antenna connections


 Gorizont 01

General

Designation	11158 / 78118A
Launch date	19 Dec 1978
Country of origin	CIS
Mission	Telecommunications
Geostationary orbit	Statsionar-05, 53°E
Launch vehicle	Proton #74
End of life

Out of service	yes
Technical data

Specifications

Antenna specifications

Transponder/Antenna connections

C-band

Ku-band

Transponder frequency chart


 Gorizont 02

General

Designation	11440 / 79062A
Launch date	5 Jul 1979
Country of origin	CIS
Mission	Telecommunications
Geostationary orbit	Statsionar-05, 53°E
Launch vehicle	Proton #79
End of life

Out of service	yes
Technical data

Specifications

Antenna specifications

Transponder/Antenna connections

C-band

Ku-band

Transponder frequency chart


 Gorizont 03

General

Designation	11648 / 79105A
Launch date	28 Dec 1979
Country of origin	CIS
Mission	Telecommunications
Geostationary orbit	Statsionar-05, 53°E
Launch vehicle	Proton #81
End of life

Out of service	yes
Technical data

Specifications

Antenna specifications

Transponder/Antenna connections

C-band

Ku-band

Transponder frequency chart


 Gorizont 04

General

Designation	11841 / 80049A
Launch date	14 Jun 1980
Country of origin	CIS
Mission	Telecommunications
Geostationary orbit	Statsionar-04, 14°W
Launch vehicle	Proton #83

Launched to broadcast the Olympic Games

End of life

Out of service	yes
Technical data

Specifications

Antenna specifications

Transponder/Antenna connections

C-band

Ku-band

Transponder frequency chart


 Gorizont 05

General

Designation	13092 / 82020A
Launch date	15 Mar 1982
Country of origin	CIS
Mission	Telecommunications
Geostationary orbit	Statsionar-14, 96.5°E
Launch vehicle	Proton #95
End of life

Out of service	yes
Technical data

Specifications

Antenna specifications

Transponder/Antenna connections

C-band

Ku-band

Transponder frequency chart


 Gorizont 06

General

Designation	13624 / 82103A
Launch date	20 Oct 1982
Country of origin	CIS
Mission	Telecommunications
Geostationary orbit	Statsionar-10, 170°W
Launch vehicle	Proton #101
End of life

Out of service	yes
Technical data

Specifications

Antenna specifications

Transponder/Antenna connections

C-band

Ku-band

Transponder frequency chart


 Gorizont 07

General

Designation	14160 / 83066A
Launch date	30 Jun 1983
Country of origin	CIS
Mission	Telecommunications
Geostationary orbit	Statsionar-11, 11°W
Launch vehicle	Proton #110
End of life

Out of service	yes
Technical data

Specifications

Antenna specifications

Transponder/Antenna connections

C-band

Ku-band

Transponder frequency chart


 Gorizont 08

General

Designation	14532 / 83118A
Launch date	30 Nov 1983
Country of origin	CIS
Mission	Telecommunications
Geostationary orbit	Statsionar-06, 90°E
Launch vehicle	Proton #114
End of life

Out of service	yes
Technical data

Specifications

Antenna specifications

Transponder/Antenna connections

C-band

Ku-band

Transponder frequency chart


 Gorizont 09

General

Designation	14940 / 84041A
Launch date	22 Apr 1984
Country of origin	CIS
Mission	Telecommunications
Geostationary orbit	Statsionar-05, 53°E
Launch vehicle	Proton #120
End of life

Out of service	yes
Technical data

Specifications

Antenna specifications

Transponder/Antenna connections

C-band

Ku-band

Transponder frequency chart


 Gorizont 10

General

Designation	15144 / 84078A
Launch date	1 Aug 1984
Country of origin	CIS
Mission	Telecommunications
Geostationary orbit	Statsionar-13, 80°E
Launch vehicle	Proton #123
End of life

Out of service	yes
Technical data

Specifications

Antenna specifications

Transponder/Antenna connections

C-band

Ku-band

Transponder frequency chart


 Gorizont 11

General

Designation	15484 / 85007A
Launch date	18 Jan 1985
Country of origin	CIS
Mission	Telecommunications
Geostationary orbit	Statsionar-05, 53°E
Launch vehicle	Proton #129
End of life

Out of service	yes
Technical data

Specifications

Antenna specifications

Transponder/Antenna connections

C-band

Ku-band

Transponder frequency chart


 Gorizont 12

General

Designation	16769 / 86044A
Launch date	10 Jun 1986
Country of origin	CIS
Mission	Telecommunications
Geostationary orbit	Statsionar-12, 40°E
Launch vehicle	Proton #143
End of life

Out of service	yes
Technical data

Specifications

Antenna specifications

Transponder/Antenna connections

C-band

Ku-band

Transponder frequency chart


 Gorizont 13

General

Designation	17083 / 86090A
Launch date	18 Nov 1986
Country of origin	CIS
Mission	Telecommunications
Geostationary orbit	Statsionar-06, 90°E
Launch vehicle	Proton #146
End of life

Out of service	yes
Technical data

Specifications

Antenna specifications

Transponder/Antenna connections

C-band

Ku-band

Transponder frequency chart


 Gorizont 14

General

Designation	17969 / 87040A
Launch date	11 May 1987
Country of origin	CIS
Mission	Telecommunications
Geostationary orbit	Statsionar-07, 140°E
Launch vehicle	Proton #152
End of life

Out of service	yes
Technical data

Specifications

Antenna specifications

Transponder/Antenna connections

C-band

Ku-band

Transponder frequency chart


 Gorizont 15

General

Designation	19017 / 88028A
Launch date	30 Mar 1988
Country of origin	CIS
Mission	Telecommunications
Geostationary orbit	Statsionar-04, 14°W
Launch vehicle	Proton #163
End of life

Out of service	yes
Technical data

Specifications

Antenna specifications

Transponder/Antenna connections

C-band

Ku-band

Transponder frequency chart


 Gorizont 16

General

Designation	19397 / 88071A
Launch date	18 Aug 1988
Country of origin	CIS
Mission	Telecommunications
Geostationary orbit	Statsionar-13, 80°E
Launch vehicle	Proton #170
End of life

Out of service	yes
Technical data

Specifications

Antenna specifications

Transponder/Antenna connections

C-band

Ku-band

Transponder frequency chart


 Gorizont 17

General

Designation	19765 / 89004A
Launch date	26 Jan 1989
Country of origin	CIS
Mission	Telecommunications
Geostationary orbit	see below
Launch vehicle	Proton #175
Location

Begin	End	Position
L: 26 Jan 1989	?	Statsionar-05, 53°E
Jun 1995		34°E, inclined
Technical data

Specifications

Antenna specifications

Transponder/Antenna connections

C-band

Ku-band

Transponder frequency chart


 Gorizont 18

General

Designation	20107 / 89052A
Launch date	5 Jul 1989
Country of origin	CIS
Mission	Telecommunications
Geostationary orbit	Statsionar-07, 140°E, inclined
Launch vehicle	Proton #179
Technical data

Specifications

Antenna specifications

Transponder/Antenna connections

C-band

Ku-band

Transponder frequency chart

EIRP coverage (dBW)

C-band, global (A6)

C-band, large hemispheric (A4)

C-band, narrow hemispheric (A8)

C-band, spot (A3)

Ku-band, spot (A9)


Gorizont 18's C-band EIRP: global A6

To get the EIRP of the A1 Global beam add 7.1 dBW


Gorizont 18's C-band EIRP: large hemispheric A4


Gorizont 18's C-band EIRP: narrow hemispheric A8


Gorizont 18's C-band EIRP: spot A3


Gorizont 18's Ku-band EIRP: spot A9


 Gorizont 19

General

Designation	20263 / 89081A
Launch date	28 Sep 1989
Country of origin	CIS
Mission	Telecommunications
Geostationary orbit	Statsionar-14, 96.5°E, inclined
Launch vehicle	Proton #180
Technical data

Specifications

Antenna specifications

Transponder/Antenna connections

C-band

Ku-band

Transponder frequency chart

EIRP coverage (dBW)

C-band, global (A6)

C-band, large hemispheric (A4)

C-band, narrow hemispheric (A8)

Ku-band, spot (A9)


Gorizont 19's C-band EIRP: global A6

To get the EIRP of the A1 Global beam add 7.1 dBW


Gorizont 19's C-band EIRP: large hemispheric A4


Gorizont 19's C-band EIRP: narrow hemispheric A8


Gorizont 19's Ku-band EIRP: spot A9


 Gorizont 20

Gorizont #31

General

Designation	20659 / 90054A
Launch date	20 Jun 1990
Country of origin	CIS
Mission	Telecommunications
Geostationary orbit	see below
Launch vehicle	Proton #188
Location

Begin	End	Position
L: 20 Jun 1990	Mar 1995	Statsionar-04, 14°W
Jun 1995		26°W, inclined
Technical data

Specifications

Antenna specifications

Transponder/Antenna connections

C-band

Ku-band

Transponder frequency chart

EIRP coverage (dBW)

C-band, global (A6)

C-band, large hemispheric (A4)

C-band, narrow hemispheric (A8)


Gorizont 20's C-band EIRP: global A6

To get the EIRP of the A1 Global beam add 7.1 dBW


Gorizont 20's C-band EIRP: large hemispheric A4


Gorizont 20's C-band EIRP: narrow hemispheric A8


 Gorizont 21

Gorizont #32

General

Designation	20923 / 90094A
Launch date	3 Nov 1990
Country of origin	CIS
Mission	Telecommunications
Geostationary orbit	see below
Launch vehicle	Proton #191
Location

Begin	End	Position
L: 3 Nov 1990		Statsionar-06, 90°E
		Statsionar-16, 145°E, inclined
Technical data

Specifications

Antenna specifications

Transponder/Antenna connections

C-band

Ku-band

Transponder frequency chart

EIRP coverage (dBW)

C-band, global (A6)

C-band, large hemispheric (A4)

C-band, narrow hemispheric (A8)

Ku-band, spot (A9)


Gorizont 21's C-band EIRP: global A6

To get the EIRP of the A1 Global beam add 7.1 dBW


Gorizont 21's C-band EIRP: large hemispheric A4


Gorizont 21's C-band EIRP: narrow hemispheric A8


Gorizont 21's Ku-band EIRP: spot A9


 Gorizont 22

Gorizont #33

General

Designation	20953 / 90102A
Launch date	23 Nov 1990
Country of origin	CIS
Mission	Telecommunications
Geostationary orbit	see below
Launch vehicle	Proton #192
Location

Begin	End	Position
L: 23 Nov 1990	Jan 1996	Statsionar-12, 40°E, inclined
drifting
Technical data

Specifications

Antenna specifications

Transponder/Antenna connections

C-band

Ku-band

Transponder frequency chart


 Gorizont 23

Gorizont #34

General

Designation	21533 / 91046A
Launch date	2 Jul 1991
Country of origin	CIS
Mission	Telecommunications
Geostationary orbit	Statsionar-21, 103°E
Launch vehicle	Proton #200

The transponder thermoregulation failed

End of life

Out of service	yes
Technical data

Specifications

Antenna specifications

Transponder/Antenna connections

C-band

Ku-band

Transponder frequency chart


 Gorizont 24

Gorizont #35

General

Designation	21759 / 91074A
Launch date	23 Oct 1991
Country of origin	CIS
Mission	Telecommunications
Geostationary orbit	Statsionar-13, 80°E, inclined
Launch vehicle	Proton #202
Technical data

Specifications

Antenna specifications

Transponder/Antenna connections

C-band

Ku-band

Transponder frequency chart

EIRP coverage (dBW)

C-band, global (A6)

C-band, large hemispheric (A4)

C-band, narrow hemispheric (A8)

C-band, spot (A3)

Ku-band, spot (A9)


Gorizont 24's C-band EIRP: global A6

To get the EIRP of the A1 Global beam add 7.1 dBW


Gorizont 24's C-band EIRP: large hemispheric A4


Gorizont 24's C-band EIRP: narrow hemispheric A8


Gorizont 24's C-band EIRP: spot A3


Gorizont 24's Ku-band EIRP: spot A9


 Gorizont 25

Gorizont #36

General

Designation	21922 / 92017A
Launch date	2 Apr 1992
Country of origin	CIS
Mission	Telecommunications
Geostationary orbit	Statsionar-21, 103°E, inclined
Launch vehicle	Proton #206
Technical data

Specifications

Antenna specifications

Transponder/Antenna connections

C-band

Ku-band

Transponder frequency chart

EIRP coverage (dBW)

C-band, global (A6)

C-band, large hemispheric (A4)

C-band, narrow hemispheric (A8)

Ku-band, spot (A9)


Gorizont 25's C-band EIRP: global A6

To get the EIRP of the A1 Global beam add 7.1 dBW


Gorizont 25's C-band EIRP: large hemispheric A4


Gorizont 25's C-band EIRP: narrow hemispheric A8


Gorizont 25's Ku-band EIRP: spot A9


 Gorizont 26

Gorizont #37

General

Designation	22041 / 92043A
Launch date	14 Jul 1992
Country of origin	CIS
Mission	Telecommunications
Geostationary orbit	Statsionar-11, 11°W, inclined
Launch vehicle	Proton #207
Technical data

Specifications

Antenna specifications

Transponder/Antenna connections

C-band

Ku-band

Transponder frequency chart

EIRP coverage (dBW)

C-band, global (A6)

C-band, large hemispheric (A4)

C-band, narrow hemispheric (A8)

Ku-band, spot (A9)


Gorizont 26's C-band EIRP: global A6

To get the EIRP of the A1 Global beam add 7.1 dBW


Gorizont 26's C-band EIRP: large hemispheric A4


Gorizont 26's C-band EIRP: narrow hemispheric A8


Gorizont 26's Ku-band EIRP: spot A9


 Gorizont 27

Gorizont #38

General

Designation	22245 / 92082A
Launch date	27 Nov 1992
Country of origin	CIS
Mission	Telecommunications
Geostationary orbit	Statsionar-05, 53°E, inclined
Launch vehicle	Proton #211
Technical data

Specifications

Antenna specifications

Transponder/Antenna connections

C-band

Ku-band

Transponder frequency chart

EIRP coverage (dBW)

C-band, global (A6)

C-band, large hemispheric (A4)

C-band, narrow hemispheric (A8)

C-band, spot (A3)

Ku-band, spot (A9)


Gorizont 27's C-band EIRP: global A6

To get the EIRP of the A1 Global beam add 7.1 dBW


Gorizont 27's C-band EIRP: large hemispheric A4


Gorizont 27's C-band EIRP: narrow hemispheric A8


Gorizont 27's C-band EIRP: spot A3


Gorizont 27's Ku-band EIRP: spot A9


 Gorizont #39

End of life

Out of service	27 May 1993
Cause	Third stage failure of the Proton #215 launcher
Decay	In the pacific Ocean


 Gorizont 28

Gorizont #40

General

Designation	22880 / 93069A
Launch date	28 Oct 1993 at 15:17 UT
Country of origin	CIS
Mission	Telecommunications
Geostationary orbit	Statsionar-06, 90°E
Launch vehicle	Proton #217
Technical data

Specifications

Antenna specifications

Transponder/Antenna connections

C-band

Ku-band

Transponder frequency chart

EIRP coverage (dBW)

C-band, global (A6)

C-band, large hemispheric (A4)

C-band, narrow hemispheric (A8)

C-band, spot (A3)

Ku-band, spot (A9)


Gorizont 28's C-band EIRP: global A6

To get the EIRP of the A1 Global beam add 7.1 dBW


Gorizont 28's C-band EIRP: large hemispheric A4


Gorizont 28's C-band EIRP: narrow hemispheric A8


Gorizont 28's C-band EIRP: spot A3


Gorizont 28's Ku-band EIRP: spot A9


 Gorizont 29

Gorizont #41, also called Rimsat 1 or Rimsat G1 or Statsionar R1

General

Designation	22907 / 93072A
Launch date	18 Nov 1993 at 13:55 UT
Country of origin	CIS
Mission	Telecommunications
Geostationary orbit	130°E
Launch vehicle	Proton #218

Was leased to the US-Malaysian Rimsat company to offer telecommunications services over Asia and the Pacific region. Rimsat was to use the satellite 3 years for a cost of $12 million. In September 1995 the satellite was taken over by Intersputnik after a complex dispute

Technical data

Specifications

Antenna specifications

Transponder/Antenna connections

C-band

Ku-band

Transponder frequency chart

The satellite provides slightly better performance than the standard Gorizont: at least 1 dBW more in C-band and 3 dBW in Ku-band (see footprint maps for details). This improvment could be due to a little more power available, perhaps because of the lack of auxilliary (X- or L-band) transponders.

EIRP coverage (dBW)

C-band, global (A6)

C-band, large hemispheric (A4)

C-band, narrow hemispheric (A8)

Ku-band, spot (A9)


Gorizont 29's C-band EIRP: global A6

At BOL the satellite had 1 dBW additional power
To get the EIRP of the A1 Global beam add 8.1 dBW


Gorizont 29's C-band EIRP: large hemispheric A4

At BOL the satellite had 2 dBW additional power


Gorizont 29's C-band EIRP: narrow hemispheric A8

At BOL the satellite had 1 dBW additional power


Gorizont 29's Ku-band EIRP: spot A9

At BOL the satellite had 3 dBW additional power


 Gorizont 30

Gorizont #42, also called Rimsat 2 or Rimsat G2 or Statsionar R2

General

Designation	23108 / 94030A
Launch date	20 May 1994 at 02:01 UT
Country of origin	CIS
Mission	Telecommunications
Geostationary orbit	142.5°E (Statsionar-R2), inclined
Launch vehicle	Proton #223

Was leased to the US-Malaysian Rimsat company. In September 1995 the satellite was taken over by Intersputnik after a complex dispute

Technical data

Specifications

Antenna specifications

Transponder/Antenna connections

C-band

Ku-band

Transponder frequency chart

The satellite provides slightly better performance than the standard Gorizont: at least 1 dBW more in C-band and 3 dBW in Ku-band (see footprint maps for details). This improvment could be due to a little more power available, perhaps because of the lack of auxilliary (X- or L-band) transponders.

EIRP coverage (dBW)

C-band, global (A6)

C-band, large hemispheric (A4)

C-band, narrow hemispheric (A8)

Ku-band, spot (A9)


Gorizont 30's C-band EIRP: global A6

At BOL the satellite had 1 dBW additional power
To get the EIRP of the A1 Global beam add 8.1 dBW


Gorizont 30's C-band EIRP: large hemispheric A4

At BOL the satellite had 2 dBW additional power


Gorizont 30's C-band EIRP: narrow hemispheric A8

At BOL the satellite had 1 dBW additional power


Gorizont 30's Ku-band EIRP: spot A9

At BOL the satellite had 3 dBW additional power


 Gorizont 31

Gorizont #43

General

Designation	23775 / 96005A
Launch date	25 Jan 1996 at 10:00 UT
Country of origin	CIS
Mission	Telecommunications
Geostationary orbit	Statsionar-12, 40°E
Launch vehicle	Proton #239
Technical data

Specifications

Antenna specifications

Transponder/Antenna connections

C-band

Ku-band

Transponder frequency chart

EIRP coverage (dBW)

C-band, global (A6)

C-band, large hemispheric (A4)

C-band, narrow hemispheric (A8)

Ku-band, spot (A9)


Gorizont 31's C-band EIRP: global A6

To get the EIRP of the A1 Global beam add 7.1 dBW


Gorizont 31's C-band EIRP: large hemispheric A4


Gorizont 31's C-band EIRP: narrow hemispheric A8


Gorizont 31's Ku-band EIRP: spot A9


 Program: GPS

Global Positionary Satellite

Also called Navstar (NAVigation System using Tuning And Ranging)

American navigation satellite program operated by USAF. The satellites were placed by pairs on 20200 km circular orbits to provide localization (with 10 m precision). They were equipped with atomic clocks.

The IIA satellites series were built by Rockwell

Planes and slots

The GPS 2-NN series orbit in six distinct planes that are about 60 deg apart. Each plane has four "slots." Following are the 2-NN members in the planes/slots.

Plane	Slot 1	Slot 2	Slot 3	Slot 4
A	2-21 / 1-10	2-12	2-15	2-04
B	2-18	2-07	2-02	2-22
C	2-24	2-13	2-19	2-20
D	2-11	2-09	2-05	2-23
E	2-01	2-08	2-03	2-10
F	2-16	2-14	2-06	2-17
Contact

http://www.laafb.af.mil/CZ/homepage/


Program: GPS

GPS BI-01	GPS BI-02	GPS BI-03	GPS BI-04
GPS BI-05	GPS BI-06	GPS BI-07	GPS BI-08
GPS BI-09	GPS BI-10	GPS BI-11
GPS BII-01	GPS BII-02	GPS BII-03	GPS BII-04
GPS BII-05	GPS BII-06	GPS BII-07	GPS BII-08
GPS BIIA-10	GPS BIIA-11	GPS BIIA-12	GPS BIIA-13
GPS BIIA-14	GPS BIIA-15	GPS BIIA-16	GPS BIIA-17
GPS BIIA-18	GPS BIIA-19	GPS BIIA-20	GPS BIIA-21
GPS BIIA-22	GPS BIIA-23	GPS BIIA-24	GPS BIIA-25


 GPS BI-01

Also called OPS 5111 or Navstar 1 or GPS 01

General

Designation	10684 / 78020A
Launch date	22 Feb 1978
Country of origin	United States
Mission	Navigation
Perigee/Apogee	20230/20578 km
Inclination	64.6°
Period	727 min
Launch vehicle	Atlas F
Launch site	Vandenberg
End of life

Out of service	July 1985


 GPS BI-02

Also called OPS 5112 or Navstar 2 or GPS 02

General

Designation	10893 / 78047A
Launch date	13 May 1978
Country of origin	United States
Mission	Navigation
Perigee/Apogee	19522/20653 km
Inclination	63.6°
Period	714.2 min
Launch vehicle	Atlas F
Launch site	Vandenberg
End of life

Out of service	July 1981


 GPS BI-03

Also called OPS 5113 or Navstar 3 or GPS 03

General

Designation	11054 / 78093A
Launch date	7 Oct 1978
Country of origin	United States
Mission	Navigation
Perigee/Apogee	20705/20942 km
Inclination	63.3°
Period	744.2 min
Launch vehicle	Atlas F
Launch site	Vandenberg

Was equipped with corner-cube reflectors for satellite laser ranging (SLR). SLR tracking of the satellites permit onboard clock errors and satellite ephemeris errors in GPS tracking to be differentiated.

End of life

Out of service	May 1992


 GPS BI-04

Also called OPS 5114 or Navstar 4 or GPS 04

General

Designation	11141 / 78112A
Launch date	11 Dec 1978
Country of origin	United States
Mission	Navigation
Perigee/Apogee	20748/21013 km
Inclination	64.6°
Period	746.5 min
Launch vehicle	Atlas F
Launch site	Vandenberg
End of life

Out of service	Oct 1989


 GPS BI-05

Also called OPS 5117 or Navstar 5 or GPS 05

General

Designation	11690 / 80011A
Launch date	9 Feb 1980
Country of origin	United States
Mission	Navigation
Perigee/Apogee	19807/20557 km
Inclination	65°
Period	718 min
Launch vehicle	Atlas F
Launch site	Vandenberg

Was equipped with corner-cube reflectors for satellite laser ranging (SLR). SLR tracking of the satellites permit onboard clock errors and satellite ephemeris errors in GPS tracking to be differentiated.

End of life

Out of service	Nov 1983


 GPS BI-06

Also called OPS 5118 or Navstar 6 or GPS 06

General

Designation	11783 / 80032A
Launch date	26 Apr 1980
Country of origin	United States
Mission	Navigation
Perigee/Apogee	19378/20480 km
Inclination	62.7°
Period	707.8 min
Launch vehicle	Atlas F
Launch site	Vandenberg
End of life

Out of service	Mar 1991


 GPS BI-07

Also called Navstar 7 or GPS 07

End of life

Out of service	18 Dec 1981
Cause	Launch failure (Atlas F)


 GPS BI-08

Also called OPS 9794 or Navstar 8 or GPS 08

General

Designation	14189 / 83072A
Launch date	14 Jul 1983
Country of origin	United States
Mission	Navigation
Perigee/Apogee	20801/21183 km
Inclination	64.3°
Period	751.1 min
Launch vehicle	Atlas F
Launch site	Vandenberg
End of life

Out of service	May 1993
Cause	Replaced by GPS BIIA-20
Technical data

Used to transmit on 1575.42 and 1227.6 MHz


 GPS BI-09

Also called USA 001 or Navstar 9 or GPS 09

General

Designation	15039 / 84059A
Launch date	13 Jun 1984
Country of origin	United States
Mission	Navigation
Perigee/Apogee	20032/20332 km
Inclination	63.9°
Period	718 min
Launch vehicle	Atlas F
Launch site	Vandenberg
End of life

Out of service	Jun 1994
Technical data

Transmits on 1575.42 and 1227.6 MHz


 GPS BI-10

Also called USA 005 or Navstar 10 or GPS 10

General

Designation	15271 / 84097A
Launch date	8 Sep 1984
Country of origin	United States
Mission	Navigation
Perigee/Apogee	19952/20411 km
Inclination	62.2°
Period	718 min
Launch vehicle	Atlas E14
Launch site	Vandenberg
Technical data

Transmits on 1575.42 and 1227.6 MHz


 GPS BI-11

Also called USA 010 or Navstar 11 or GPS 11

General

Designation	16129 / 85093A
Launch date	9 Oct 1985
Country of origin	United States
Mission	Navigation
Perigee/Apogee	20449/21211 km
Inclination	64.1°
Period	744.4 min
Launch vehicle	Atlas E55
Launch site	Vandenberg
End of life

Out of service	Apr 1994
Technical data

Transmits on 1575.42 and 1227.6 MHz


 GPS BII-01

Also called USA 035 or Navstar 2-1 or GPS 14

General

Designation	19802 / 89013A
Launch date	14 Feb 1989
Country of origin	United States
Mission	Navigation
Perigee/Apogee	20088/20274 km
Inclination	55.0°
Period	717.9 min
Launch vehicle	Delta 2 #183
Technical data

Transmits on 1575.42 and 1227.6 MHz


 GPS BII-02

Also called USA 038 or Navstar 2-2 or GPS 13

General

Designation	20061 / 89044A
Launch date	10 Jun 1989
Country of origin	United States
Mission	Navigation
Perigee/Apogee	19847/20517 km
Inclination	54.5°
Period	718 min
Launch vehicle	Delta 2 #185
Technical data

Transmits on 1575.42 and 1227.6 MHz


 GPS BII-03

Also called USA 042 or Navstar 2-3 or GPS 16

General

Designation	20185 / 89064A
Launch date	18 Aug 1989
Country of origin	United States
Mission	Navigation
Perigee/Apogee	20154/20207 km
Inclination	55.0°
Period	717.9 min
Launch vehicle	Delta 2 #186
Technical data

Transmits on 1575.42 and 1227.6 MHz


 GPS BII-04

Also called USA 047 or Navstar 2-4 or GPS 19

General

Designation	20302 / 89085A
Launch date	21 Oct 1989
Country of origin	United States
Mission	Navigation
Perigee/Apogee	20176/20188 km
Inclination	53.4°
Period	718 min
Launch vehicle	Delta 2 #188
Technical data

Transmits on 1575.42 and 1227.6 MHz


 GPS BII-05

Also called USA 049 or Navstar 2-5 or GPS 17

General

Designation	20361 / 89097A
Launch date	11 Dec 1989
Country of origin	United States
Mission	Navigation
Perigee/Apogee	19995/20369 km
Inclination	55.7°
Period	718 min
Launch vehicle	Delta 2 #190
Technical data

Transmits on 1575.42 and 1227.6 MHz


 GPS BII-06

Also called USA 050 or Navstar 2-6 or GPS 18

General

Designation	20452 / 90008A
Launch date	24 Jan 1990
Country of origin	United States
Mission	Navigation
Perigee/Apogee	20038/20324 km
Inclination	54°
Period	717.9 min
Launch vehicle	Delta 2 #191
Technical data

Transmits on 1575.42 and 1227.6 MHz


 GPS BII-07

Also called USA 054 or Navstar 2-7 or GPS 20

General

Designation	20533 / 90025A
Launch date	26 Mar 1990
Country of origin	United States
Mission	Navigation
Perigee/Apogee	20071/20292 km
Inclination	54.9°
Period	718 min
Launch vehicle	Delta 2 #193
Technical data

Transmits on 1575.42 and 1227.6 MHz


 GPS BII-08

Also called USA 063 or Navstar 2-8 or GPS 21

General

Designation	20724 / 90068A
Launch date	2 Aug 1990
Country of origin	United States
Mission	Navigation
Perigee/Apogee	19891/20473 km
Inclination	54.7°
Period	718 min
Launch vehicle	Delta 2 #197
Technical data

Transmits on 1575.42 and 1227.6 MHz


 GPS BII-09

Also called USA 064 or Navstar 2-9 or GPS 15

General

Designation	20830 / 90088A
Launch date	1 Oct 1990
Country of origin	United States
Mission	Navigation
Perigee/Apogee	20002/20363 km
Inclination	55.6°
Period	718 min
Launch vehicle	Delta 2 #199
Technical data

Transmits on 1575.42 and 1227.6 MHz


 GPS BIIA-10

Also called USA 066 or Navstar 2A-10 or GPS 23

General

Designation	20959 / 90103A
Launch date	26 Nov 1990
Country of origin	United States
Mission	Navigation
Perigee/Apogee	19968/20394 km
Inclination	55.1°
Period	718 min
Launch vehicle	Delta 2 #201
Technical data

Transmits on 1575.42 and 1227.6 MHz


 GPS BIIA-11

Also called USA 071 or Navstar 2A-11 or GPS 24

General

Designation	21552 / 91047A
Launch date	4 Jul 1991
Country of origin	United States
Mission	Navigation
Perigee/Apogee	20031/20331 km
Inclination	56°
Period	718 min
Launch vehicle	Delta 2 #206
Technical data

Transmits on 1575.42 and 1227.6 MHz


 GPS BIIA-12

Also called USA 079 or Navstar 2A-12 or GPS 25

General

Designation	21890 / 92009A
Launch date	23 Feb 1992
Country of origin	United States
Mission	Navigation
Perigee/Apogee	20031/20335 km
Inclination	54.2°
Period	718 min
Launch vehicle	Delta 2 #207
Technical data

Transmits on 1575.42 and 1227.6 MHz


 GPS BIIA-13

Also called USA 080 or Navstar 2A-13 or GPS 28

General

Designation	21930 / 92019A
Launch date	10 Apr 1992
Country of origin	United States
Mission	Navigation
Perigee/Apogee	20026/20338 km
Inclination	55.7°
Period	718 min
Launch vehicle	Delta 2 #208
Technical data

Transmits on 1575.42 and 1227.6 MHz


 GPS BIIA-14

Also called USA 083 or Navstar 2A-14 or GPS 26

General

Designation	22014 / 92039A
Launch date	7 Jul 1992
Country of origin	United States
Mission	Navigation
Perigee/Apogee	19961/20402 km
Inclination	54.9°
Period	718 min
Launch vehicle	Delta 2 #211
Technical data

Transmits on 1575.42 and 1227.6 MHz


 GPS BIIA-15

Also called USA 084 or Navstar 2A-15 or GPS 27

General

Designation	22108 / 92058A
Launch date	9 Sep 1992
Country of origin	United States
Mission	Navigation
Perigee/Apogee	19909/20453 km
Inclination	54.2°
Period	718 min
Launch vehicle	Delta 2 #214
Technical data

Transmits on 1575.42 and 1227.6 MHz


 GPS BIIA-16

Also called USA 085 or Navstar 2A-16 or GPS 32

General

Designation	22231 / 92079A
Launch date	22 Nov 1992 at 20:53 UT
Country of origin	United States
Mission	Navigation
Perigee/Apogee	20088/20275 km
Inclination	54.7°
Period	717.9 min
Launch vehicle	Delta 2 #216
Technical data

Transmits on 1575.42 and 1227.6 MHz


 GPS BIIA-17

Also called USA 087 or Navstar 2A-17 or GPS 29

General

Designation	22275 / 92089A
Launch date	18 Dec 1992 at 10:16 UT
Country of origin	United States
Mission	Navigation
Perigee/Apogee	20044/20320 km
Inclination	54.6°
Period	718 min
Launch vehicle	Delta 2 #217
Technical data

Transmits on 1575.42 and 1227.6 MHz


 GPS BIIA-18

Also called USA 088 or Navstar 2A-18 or GPS 22

General

Designation	22446 / 93007A
Launch date	3 Feb 1993 at 02:55 UT
Country of origin	United States
Mission	Navigation
Perigee/Apogee	19995/20370 km
Inclination	54.5°
Period	718 min
Launch vehicle	Delta 2 #218
Technical data

Transmits on 1575.42 and 1227.6 MHz


 GPS BIIA-19

Also called USA 090 or Navstar 2A-19 or GPS 31

General

Designation	22581 / 93017A
Launch date	30 Mar 1993 at 03:29 UT
Country of origin	United States
Mission	Navigation
Perigee/Apogee	20072/20293 km
Inclination	55.2°
Period	718 min
Launch vehicle	Delta 2 #219

Equipped with a Star 37 solid motor

Technical data

Transmits on 1575.42 and 1227.6 MHz


 GPS BIIA-20

Also called USA 091 or Navstar 2A-20 or GPS 37

General

Designation	22657 / 93032A
Launch date	13 May 1993
Country of origin	United States
Mission	Navigation
Perigee/Apogee	20017/20345 km
Inclination	55.2°
Period	718 min
Launch vehicle	Delta 2 #220
Technical data

Transmits on 1575.42 and 1227.6 MHz


 GPS BIIA-21

Also called USA 092 or Navstar 2A-21 or GPS 39

General

Designation	22700 / 93042A
Launch date	26 Jun 1993 at 13:27 UT
Country of origin	United States
Mission	Navigation
Perigee/Apogee	20112/20250 km
Inclination	54.4°
Period	717.9 min
Launch vehicle	Delta 2 #221
Technical data

Transmits on 1575.42 and 1227.6 MHz


 GPS BIIA-22

Also called USA 094 or Navstar 2A-22 or GPS 35

General

Designation	22779 / 93054A
Launch date	30 Aug 1993 at 12:35 UT
Country of origin	United States
Mission	Navigation
Perigee/Apogee	20127/20236 km
Inclination	54.6°
Period	718 min
Launch vehicle	Delta 2 #222
Technical data

Transmits on 1575.42 and 1227.6 MHz


 GPS BIIA-23

Also called USA 096 or Navstar 2A-23 or GPS 34

General

Designation	22877 / 93068A
Launch date	26 Oct 1993
Country of origin	United States
Mission	Navigation
Perigee/Apogee	20104/20260 km
Inclination	55.2°
Period	718 min
Launch vehicle	Delta 2 #223
Technical data

Transmits on 1575.42 and 1227.6 MHz


 GPS BIIA-24

Also called USA 100 or Navstar 2A-24 or GPS 36

General

Designation	23027 / 94016A
Launch date	10 Mar 1994
Country of origin	United States
Mission	Navigation
Perigee/Apogee	20023/20339 km
Inclination	55.1°
Period	717.95 min
Launch vehicle	Delta 2 #226
Technical data

Transmits on 1575.42 and 1227.6 MHz


 GPS BIIA-25

Also called Navstar 2A-25 or GPS 38?

General

Designation	23833 / 96019A
Launch date	28 Mar 1996
Country of origin	United States
Mission	Navigation
Perigee/Apogee
Inclination
Period
Launch vehicle	Delta 2 #234

The satellite was worth $55 million. It should go into plane C

A solid Thiokol Star 37 apogee motor was used to circularize the orbit

After this launch, 3 BIIA satellites are still to be launched

Technical data

Transmits on 1575.42 and 1227.6 MHz

Telemetry on 2227.5 MHz


 Granat

General

Designation	20352 / 89096A
Launch date	1 Dec 1989
Country of origin	CIS
Mission	Scientific: astronomy
Perigee/Apogee	57435/146072 km
Inclination	86.7°
Period	5897.8 min
Launch vehicle
Launch site	Tyuratam

Astronomy satellite carrying the French Sigma telescope


 GRO

Gamma Ray Observatory, also called Compton gamma-ray observatory

General

Designation	21225 / 91027B
Launch date	5 Apr 1991
Country of origin	United States
Operator	NASA
Mission	Scientific: Astronomy
Perigee/Apogee	437/462 km
Inclination	28.4°
Period	93.5 min
Launch vehicle	STS 37
Mass at launch	15620 kg
Technical data

Specifications

Prime contractor	TRW
Dimension	7.7 x 5.5 x 4.6 m
Solar array	21.5 m
Stabilization	3 axis
DC power	EOL: 3980 W
Design lifetime	2 years (min)
BATSE (Burst and Transcient Source Experiment)

Payload mass	976 kg
Industrial responsibility	Marshall SFC
Gamma-ray energy range	20-600 keV

Equipped with 8 detectors

OSSE (Oriented Scintillation Spectrometer Experiment)

Payload mass	1820 kg
Industrial responsibility	Ball Aerospace
Gamma-ray energy range	100 keV-10 MeV
COMTEL (imaging COMpton TELescope)

Payload mass	1460 kg
Industrial responsibility	MBB
Gamma-ray energy range	1-30 MeV
Angular resolution	1.7-4.4°
EGRET (Energetic Gamma Ray Experiment Telescope)

Payload mass	1830 kg
Industrial responsibility	Goddard SFC
Gamma-ray energy range	20 MeV-30 GeV


 Program: Gstar

American telecommunication satellite program operated by GE Americom, formerly GTE Spacenet Corp.

Contact

GE Americom

4 Research Way, Princeton, NJ 08540, USA

Tel: +1-609-987-4200

Fax: +1-609-987-4495

NYSE: GE


Program: Gstar

Gstar 1

Gstar 2

Gstar 3

Gstar 4


Gstar's specifications

Prime contractor	GE Astro Space
Platform	GE 3000
Mass dry	543 kg
Mass at launch	1270 kg
Mass in orbit	759 kg
Dimension	1.63 x 1.32 x 0.99 m
Solar array	13.93 m span
Stabilization	3 axis
DC power	BOL: 1750 W
Design lifetime	10 years


Gstar's Ku-band

Main transponders	14+2
Backup transponders	5+1
Power	14 transponders of 20 W (TWTA) 2 transponders of 27 W (TWTA)
Bandwidth	54 MHz
Coverage
EIRP	20 W: 38 dBW 27 W: 48 dBW
Polarization	linear


Gstar's transponder frequency chart (GHz)

Horizontal Uplink	Horizontal Downlink	Transponder	Vertical Downlink	Vertical Uplink
	11.730	1		14.030
14.044		9	11.744
	11.791	2		14.091
14.105		10	11.805
	11.852	3		14.152
14.166		11	11.866
	11.913	4		14.213
14.227		12	11.927
	11.974	5		14.274
14.288		13	11.988
	12.035	6		14.335
14.349		14	12.049
	12.096	7		14.396
14.410		15	12.110
	12.157	8		14.457
14.471		16	12.171


 Gstar 1

General

Designation	15677 / 85035A
Launch date	8 May 1985
Country of origin	United States
Mission	Telecommunications
Geostationary orbit	103°W
Launch vehicle	Ariane V13
Technical data

Specifications

Ku-band

Transponder frequency chart


 Gstar 2

General

Designation	16649 / 86026A
Launch date	28 Mar 1986
Country of origin	United States
Mission	Telecommunications
Geostationary orbit	see below
Launch vehicle	Ariane V17
Location

Begin	End	Position
L: 28 Mar 1986
< May 1992	May 1992 >	105°W
<Oct 1993		125°W, inclined
Technical data

Specifications

Ku-band

Transponder frequency chart


 Gstar 3

General

Designation	19483 / 88081A
Launch date	8 Sep 1988
Country of origin	United States
Mission	Telecommunications
Geostationary orbit	93°W, inclined
Launch vehicle	Ariane V25

This satellite had a motor problem and so is inclined

Technical data

Specifications

Ku-band

Transponder frequency chart


 Gstar 4

General

Designation	20946 / 90100B
Launch date	20 Nov 1990
Country of origin	United States
Mission	Telecommunications
Geostationary orbit	see below
Launch vehicle	Ariane V40
Location

Begin	End	Position
L: 20 Nov 1990
< May 1992	May 1992 >	125°W
<Oct 1993		105°W
Technical data

Specifications

Ku-band

Transponder frequency chart


 Gurwin 1

Also called Techsat 1

General

Launch date	28 Mar 1995
Country of origin	Israel
Mission	Telecommunications
Launch vehicle	Start #2
End of life

Cause	Launcher failure
Decay	28 Mar 1995

The satellite carried a CCD camera, a radiation detector, an ozone monitor as well as satellite technology tests. It carried a multi-user store-and-forward Amateur Radio digital communications transponder. Gurwin could primarily operate at 9600 bits per second FSK although it was also cable of 1200 bps BPSK.

Technical data

Specifications

Prime contractor	Technion-Israel Institute of Technology in Haifa
Platform
Mass at launch	50 kg
Mass in orbit
Length	0.45 m
Width	0.5 m
Height	0.5 m
Stabilization
DC power
Design lifetime
Frequency chart

145 MHz uplink	1269 MHz uplink	435 MHz downlink
145.850	1269.700	435.225
145.890	1269.800	435.325
145.910	1269.900
145.930	1269.950


 Healthsat

General

Designation	22827 / 93061E
Launch date	25 Sep 1993
Country of origin	United States
Operator	SateLife
Mission	Telecommunications
Perigee/Apogee	788/803 km
Inclination	98.7°
Period	100.8 min
Launch vehicle	Ariane V59
Mass at launch	47.5 kg

Transmits medical data (provided by the United States, Canada and the UK) to African universities, hospitals and documentation centers.

Technical data

Specifications

Prime contractor	SSTL (Surrey Satellite Technology Ltd.)
Platform	SSTL
Mass at launch	50.5 kg
Mass in orbit
Length	352 mm
Width	356 mm
Height	670 mm
Stabilization	gravity gradient
DC power
Design lifetime	5 years


 Program: Heao

High Energy Astronomy Observatory

American scientific program made of 3 large observatories designed to study the "high energy universe," i.e., X-rays, gamma rays, and cosmic particles.

The scientific objectives of the HEAO program were to learn more about some of the most puzzling objects in the universe: pulsars, neutron stars, black holes, quasars, radio galaxies, and supernovas. Many of these radiate only in the X-ray, gamma ray, and cosmic ray regions of the electromagnetic spectrum and cannot be studied from the ground.


Program: Heao

Heao 1

Heao 2

Heao 3


 Heao 1

General

Designation	10217 / 77075A
Launch date	12 Aug 1977
Country of origin	United States
Mission	Scientific: X-ray astronomy
Perigee/Apogee	429/447 km
Inclination	22.7°
Period	93.4 min
Launch vehicle	Atlas Centaur
Launch site	Cape Canaveral
Mass at launch	approx. 3 t
End of life

Decay	15 Mar 1979


 Heao 2

Also called "Einstein observatory"

General

Designation	11101 / 78103A
Launch date	13 Nov 1978
Country of origin	United States
Mission	Scientific: X-ray astronomy
Perigee/Apogee	526/548 km
Inclination	23.5°
Period	95.4 min
Launch vehicle	Atlas Centaur
Launch site	Cape Canaveral
Mass at launch	approx. 3 t

Equipped with a 58cm diameter telescope with a 3.3m focal length. The satellite also contained five other instruments, 4 of which shared the use of the telescope to make a variety of measurements of X-rays emitted by stellar objects. The fifth instrument, independent of the telescope, measured properties of X-rays beyond the telescope's energy range.

Built by TRW Defense and Space Systems for NASA's Marshall Space Flight Center

End of life

Decay	25 Mar 1982


 Heao 3

General

Designation	11532 / 79082A
Launch date	20 Sep 1979
Country of origin	United States
Mission	Scientific: gamma-ray astronomy
Perigee/Apogee	487/503 km
Inclination	43.6°
Period	94.5 min
Launch vehicle	Atlas Centaur
Launch site	Cape Canaveral
Mass at launch	approx. 3 t
End of life

Decay	7 Dec 1981


 Program: Hélios

In Greek mythology Helios was all-seeing and all-knowing

French military observation program which first generation is financed by France (79%), Italy (14%) and Spain (7%). Operated by the DGA (Délégation Générale à l'Armement) and the CNES. Each country can use the satellite in proportion of its financial participation. Each country can order observations and obtain the results via its Earth station. Each country's results are cyphered so that only the orderer can use the data.

The second generation (Helios 2) is planned for 2002 and will be achieved by France and Germany. It is supposed to cost between $1.5 and $3 million. It would be equipped with for optical and IR observation.

Other French military projects: satellite Osiris (Horus) (radar/electromagnetic reconnaissance) should cost $2.4 million (with Germany taking part). Zenon (eavesdropping satellite) and Clementine (the Cerise companion)


Program: Hélios

Hélios 1A

Hélios 1B


 Hélios 1A

General

Designation	23605 / 95033A
Launch date	7 Jul 1995
Country of origin	France
Mission	Military: reconnaissance
Perigee/Apogee	673/676 km
Inclination	98.1°
Period	98.2 min
Launch vehicle	Ariane V75

Hélios 1A carries an eavesdroppring payload called Euracom, built by Dassault Electronique

Technical data

Specifications

Prime contractor	Matra Marconi Space (under control of CNES)
Platform	Spot MkII (derived from Spot and ERS)
Mass at launch	2537 kg
Mass in orbit
Dimension
Stabilization	guidance by momentum wheels
DC power	2200 W
Design lifetime	5 years

2 tape recorders, only optical observation

The Hélios system downlinks in S-band at 2206.53 MHz and in X-band at 8253.0 MHz


 Hélios 1B

General

Designation
Launch date	planned for late 1996 / early 1997
Country of origin	France
Mission	Military: reconnaissance
Perigee/Apogee
Inclination
Period
Launch vehicle	Ariane

When this satellite is launched the revisit period will be about 1 day. Same orbit but 180 degrees separation


 Program: Heos

Highly Eccentric Orbit Satellite

European scientific program


Program: Heos

Heos 1

Heos 2


 Heos 1

General

Designation	03595 / 68109A
Launch date	5 Dec 1968
Country of origin	Europe
Mission	Scientific: magnetophere study
Perigee/Apogee	20020/202780 km
Inclination	60.5°
Period	6704.3 min
Launch vehicle	Thor Delta #61
Mass at launch	128 kg

Study of the inter-planetary magnetic field, solar wind and space particles.

End of life

Decay	28 Oct 1975


 Heos 2

General

Designation	05814 / 72005A
Launch date	31 Jan 1972
Country of origin	Europe
Mission	Scientific: magnetophere study
Perigee/Apogee	405/240164 km
Inclination	89.9°
Period	7477.1 min
Launch vehicle	Thor Delta #87
Mass at launch	117 kg

Study of the high altitude magnetosphe limits and inter-planetary magnetic fields and particles.

End of life

Decay	2 Aug 1974


 HETE

High-Energy Transient Experiment

General

Designation
Launch date	planned in Jul 1995
Country of origin	United States
Mission	Scientific
Perigee/Apogee
Inclination
Period
Launch vehicle	Pegasus XL
Launch site	Cape Canaveral

The prime objective of HETE is to carry out the first multiwavelength study of gamma-ray bursts with UV, X-ray, and gamma-ray instruments mounted on a single, compact spacecraft. A unique feature of the HETE mission is its capability to localize GRBs with ~10 arc second accuracy, in near real time aboard the spacecraft, and to transmit these positions directly to a network of receivers at existing ground-based observatories, enabling rapid, sensitive follow-up studies in the radio, IR, and optical bands.

Technical data

Omnidirectional Gamma-Ray Spectrometer

Build by	CESR (France)
Instrument type	NaI(Tl); cleaved
Energy range	6 keV to > 1 MeV
Timing resolution	4 ms
Spectral resolution	~40% @ 6 keV; ~7% @ 1 MeV
Effective area	120 cm**2 (total for 4 units)
Sensitivity (10 sigma)	3 x 10**-8 erg/cm**2/s for 8-1000 keV
FOV	~ 2 pi sr
Angular resolution	~ 1 sr
Wide Field X-ray Monitor

Build by	RIKEN (Japan) and LANL (USA)
Instrument type	2 1-dim Coded aperture cameras, with PSPCs
Energy range	2 to 25 keV
Timing resolution	1 ms
Spectral resolution	~18% @ 6 keV
Effective area	200 cm**2 (each of 2 units)
Sensitivity (10 sigma)	8 x 10**-9 erg/cm**2/s for 2-10 keV
FOV	~ 2 sr (combined)
Angular resolution (1 sigma)	about 10 arcmin (location accuracy better than that)
Ultraviolet Transient Camera Array

Build by	MIT (USA)
Instrument type	4 UV CCD Detectors with 35 mm f/2 optics
Energy range	5 to 7 eV
Timing resolution	~ 4 s
Spectral resolution	n/a (Broadband imaging photometer)
Effective area	2.5 cm**2 (each of 4 units)
Sensitivity (10 sigma)	1 x 10**-9 erg/cm**2/s
FOV	~ 1.7 sr (total for 4 units)
Angular resolution (1 sigma)	+/- 3 arcsec

The spacecraft hardware and software is being developed by Aeroastro (USA).

Downlink frequencies: 137.96 & 2272 MHz


 Hipparcos

HIgh Precision PARallax COllecting Satellite, named as a Greek astronomer of the 2nd century before JC: Hipparkhos

General

Designation	20169 / 89062B
Launch date	8 Aug 1989
Country of origin	Europe
Mission	Scientific: astronomy
Perigee/Apogee	498/35889 km
Inclination	6.5°
Period	638.7 min
Launch vehicle	Ariane V33

Was intended on geostationary 12°W slot. The data it provided was recalculated to match its orbit position.

Hipparcos observed 118274 stars with a precision between 0.0008 and 0.002 arcsec depending on the objects magnitude. 10000 double stars were observed including 7000 which were discovered by the satellite. It also discovered numerous variable stars.

End of life

Out of service	15 Aug 1993
Cause	Stopped transmitting in June 1993
Technical data

Specifications

Prime contractor	Matra Marconi Space
Mass at launch	1140 kg
Payload mass	200 kg
Diameter	2.5 m
Height	3 m
Stabilization	3 axis
DC power	380 W
Design lifetime	2.5 years
Schmidt telescope & photon detector

Telescope aperture	0.29 m
Field of view	0.9 x 0.9°
Frequency band	visible: 375-750 nm
Telemetry/data	S-band


 Program: Hispasat

Spanish telecommunication program operated by Hispasat S.A.

Contact

Hispasat S.A.

Gobelas 41-45 Planta, 28023 Madrid -- SPAIN

Tel: +34-1-307-6040

Fax: +34-1-307-6683


Program: Hispasat

Hispasat 1A

Hispasat 1B


Hispasat's specifications

Prime contractor	Matra Marconi Space
Platform	Eurostar 2000
Mass at launch	2120 kg
Mass in orbit	1325 kg
Payload mass	280 kg
Dimension	2.21 x 1.7 x 1.9 m
Solar array	22.02 m
Stabilization	3 axis
DC power	EOL: 3790 W
Design lifetime	10 years
Telemetry	Ku-band (backup: S-band)


Hispasat's direct TV mission

Main transponders	3
Backup transponders	1
Power	110 W (TWTA)
Bandwidth	27 MHz
EIRP	58 dBW
Polarization	circular L
Uplink	12.1-12.5 GHz
Downlink	17.3-17.7 GHz


Hispasat's telecommunication to Europe mission

Main transponders	8
Backup transponders	4
Power	50 W (TWTA)
Bandwidth	4 x 36 MHz 2 x 46 MHz 2 x 72 MHz
EIRP	51 dBW
Polarization	linear
Uplink	14.0-14.25 GHz & 14.25-14.5 GHz
Downlink	12.5-12.75 GHz & 11.45-11.7 GHz


Hispasat's telecommunication to America mission (Ku-band)

Main transponders	2
Backup transponders	1
Power	110 W (TWTA)
Bandwidth	36 MHz
Coverage and EIRP	South and Central America: 53 dBW
Polarization	linear V


Hispasat's X-band

Main transponders	1
Backup transponders	1
Power	40 W (TWTA)
Bandwidth	40 MHz
Coverage
EIRP	42 dBW
Polarization


Hispasat's transponder frequency chart (GHz)

Transponder	Uplink	Downlink	Bandwidth	Main	Reserve	Coverage
16	14.317 V	11.517 H	72	1B	1A	switchable Europe / America
7	14.317 H	11.517 V	72	1A	1B	Europe
17	14.397 V	11.597 H	72	1A	1B	Europe
8	14.397 H	11.597 V	72	1B	1A	Europe
18	14.464 V	11.664 H	46	1B		switchable Europe / America
9	14.468 H	11.668 V	54	1A		Europe
15	14.249 V	12.015 V	36	1B	1A	America
6	14.249 H	12.078 V	36	1A	1B	America
23	17.32748 RHCP	12.14944 LHCP	27	?		DBS
27	17.40420 RHCP	12.22616 LHCP	27	?		DBS
31	17.48092 RHCP	12.30288 LHCP	27	?		DBS
35	17.55764 RHCP	12.37960 LHCP	27	?		DBS
39	17.63436 RHCP	12.45632 LHCP	27	?		DBS
10	14.035 V	12.540 H	54	1A		Europe
1	14.039 H	12.544 V	46	1B		Europe
11	14.086 V	12.591 H	36	1B	1A	Europe
2	14.086 H	12.591 V	36	1A	1B	Europe
12	14.126 V	12.631 H	36	1B		Europe
3	14.126 H	12.631 V	36	1A		Europe
13	14.166 V	12.671 H	36	1A	1B	Europe
4	14.166 H	12.671 V	36	1B	1A	Europe
14	14.206 V	12.711 H	36	1A		Europe
5	14.206 H	12.711 V	36	1B		Europe


Hispasat's EIRP (Direct TV)


Hispasat's EIRP (Telecommunication to Europe)


Hispasat's EIRP (Telecommunication to America)


 Hispasat 1A

General

Designation	22116 / 92060A
Launch date	10 Sep 1992
Country of origin	Spain
Mission	Telecommunications
Geostationary orbit	30°W
Launch vehicle	Ariane V53
Technical data

Specifications

Direct TV

Telecommunication to Europe

Telecommunication to America

X-band

Transponder frequency chart

Beacon: 12.7475 GHz vertical (backup in S-band)

EIRP coverage (dBW)

Direct TV

Telecommunication to Europe

Telecommunication to America


 Hispasat 1B

General

Designation	22723 / 93048A
Launch date	22 Jul 1993
Country of origin	Spain
Mission	Telecommunications
Geostationary orbit	30°W
Launch vehicle	Ariane V58
Technical data

Specifications

Direct TV

Telecommunication to Europe

Telecommunication to America

X-band

Transponder frequency chart

Beacon: 12.749 GHz vertical (backup in S-band)

EIRP coverage (dBW)

Direct TV

Telecommunication to Europe

Telecommunication to America


 HST

Hubble Space Telescope, named as the American astrophysician Edwin Powell Hubble

General

Designation	20580 / 90037B
Launch date	24 Apr 1990
Country of origin	United States
Operator	NASA
Mission	Scientific: astronomy
Perigee/Apogee	592/609 km
Inclination	28.4°
Period	96.7 min
Launch vehicle	STS 31R

The satellite was designed by Lynan Spitzer and proposed to NASA in the early 60ies.

First servicing mission: STS 61. Next missions planned: Feb 1997 (STS 82) and May 2000 (STS 106)

Cost: $3 billion

Technical data

Specifications

Prime contractor	Lockheed (spacecraft) Perkin Elmer (mirror & telescope)
Mass at launch	11250 kg
Diameter	4.25 m
Height	13.1 m
Solar array	12 x 2.83 m
Stabilization	3 axis
DC power	BOL: 5500 W
Design lifetime	15 years
Payload

Wide-Field Planetary Camera, Faint Object Camera (ESA), Faint Object Spectrograph, High Resolution Spectrograph, High Speed Photometer

The WFPC 2 replaced the original camera on 1st servicing mission and Costar replaced the High Speed Photometer

Primary mirror diameter	2.4 m
Primary mirror mass	800 kg
Frequency bands	UV, visible and near IR
Resolution	0.1 arcsecs
Pointing stability	0.007 arcsecs


 Program: IDSCP

Initial Defence Satellite Communication Program

American military program: 26 satellites of 45 kg on a 33000 km orbit launched between 1966 and 1968 to built the IDSCS network.


 Program: IMEWS

Integrated Multipurpose Early Warning Satellite

American military program designed to warn on rocket launch or warhead fall. Equipped with IR detectors.


 Indostar 1

General

Designation
Launch date	early 1997
Country of origin	Indonesia
Operator	PT Mediacitra Indostar (also called Indovision?)
Mission
Geostationary orbit	106°E
Launch vehicle	Ariane
Launch site

Up to 4 small satellites have been ordered: Indostar 2 at 115°E and Indostar 3 at 106°E

Technical data

Specifications

Prime contractor	CTA International
Platform
Mass at launch	1400 kg
Mass in orbit
Dimension
Solar array
Stabilization
DC power
Design lifetime	10 years
L-band (1452-1492 GHz)

Main transponders	2
Backup transponders
Power
Bandwidth
Coverage
EIRP
Polarization

For digital audio broadcasting

S-band (2520-2670 GHz)

Main transponders	3
Backup transponders
Power
Bandwidth
Coverage
EIRP
Polarization

For TV broadcasting


 Informator

Also called AO-21 or RS-14 or Rudak 2 or Oscar 21

General

Designation	21087 / 91006A
Launch date	29 Jan 1991
Country of origin	CIS
Mission	Telecommunications
Perigee/Apogee	955/1005 km
Inclination	82.9°
Period	104.7 min
Launch vehicle
Launch site	Plesetsk
End of life

Out of service	mid-October 1994
Technical data

Analog transponders and a digital signal processing (DSP) experiment. The DSP experiment being a bit of a chameleon, can serve many different functions, one of them being an FM repeater, another being a mailbox experiment like the Pacsat's.

Transponder 1:

Mode B up	435.102 - 435.022 MHz
Mode B down	145.852 - 145.932 MHz
Beacons	145.822 MHz CW, 145.952 MHz 1100 bps PSK

Transponder 2:

Mode B up	435.123 - 435.043 MHz
Mode B down	145.866 - 145.946 MHz
Beacons	145.948 MHz CW, 145.838 MHz 1100 bps PSK

RUDAK Transponder:

Uplink 1	435.016 MHz 1200 bps Manchester FSK + FM repeater input frq.
Uplink 2	435.155 MHz 2400 bps BPSK
Uplink 3A	435.193 MHz 4800 bps RSM NRZI
Uplink 3B	435.193 MHz 9600 bps RSM NRZI
Uplink 4	435.041 MHz Digital Signal Processor input
Downlink	145.987 MHz
Mode 1	Pacsat/FO-20 compatible
Mode 2	AO-13 400 bps BPSK compatible
Mode 3	AO-13 RUDAK I compatible
Mode 4	4800 bps
Mode 5	9600 bps
Mode 6	CW
Mode 7	FSK (F1 or F2B) RTTY, FAX, SSTV, etc.
Mode 8	FM using D/A converter and DSP output


 Injun 3

General

Designation	00504 / 62067B
Launch date	13 Dec 1962
Country of origin	United States
Mission
Perigee/Apogee	240/2406 km
Inclination	70.3°
Period	112.1 min
Launch vehicle	Thor Agena D
Launch site	Vandenberg
End of life

Decay	25 Aug 1968


 Program: Inmarsat

INternational MARitime SATellite

Inmarsat was created by the International Maritim Organization (dependent of the United Nations) on 16 Jul 1979. Its center is in London; started working on 1 Feb 1982. Inmarsat must provide links between maritime mobiles and ground networks using geostationary satellites. The services are telephone, telex, fax and an access to the emergency system Sarsat/Cospas.

Inmarsat's structure is close to Intelsat's one. It isn't dominated by the United States so that the CIS could enter it.

The organization gathered 48 members in 1986 and 64 in 1991. The first operational system opened in 1985. Transponders were leased on 6 satellites: Marisat, Marecs and Intelsat. With the success encountered Inmarsat decided in 1983 to operate its own satellites.

Over 20 ground stations have been installed and in 1992 over 15000 terminals had been sold. The states that mostly participate in the funding are the United States, Norway, the UK and Japan.

Inmarsat is also working on aeronautical links and a project of personnal communication medium. Inmarsat might develop low orbit satellites on polar orbits to cover Northern and Southern regions.

Members (76): Algeria, Argentina, Australia, Bahrain, Bahamas, Bangladesh, Belarus, Belgium, Brazil, Brunei Darussalam, Bulgaria, Cameroon, Canada, Chile, China People's Republic, Colombia, Croatia, Cuba, Cyprus, Czech Republic, Denmark, Egypt, Finland, France, Gabon, Germany, Greece, Iceland, India, Indonesia, Iran, Iraq, Israel, Italy, Japan, Korea, Republic of Kuwait, Lebanon, Liberia, Malaysia, Malta, Mauritius, Mexico, Monaco, Mozambique, Netherlands, New Zealand, Nigeria, Norway, Oman, Pakistan, Panama, Peru, Philippines, Poland, Portugal, Qatar, Romania, Russian Federation, Saudi Arabia, Senegal, Singapore, Slovak Republic, South Africa, Spain, Sri Lanka, Sweden, Switzerland, Thailand, Tunisia, Turkey, Ukraine, United Arab Emirates, United Kingdom, USA, Yugoslavia

Contact

Inmarsat Ltd

99 City Road, London EC1Y 1AX, United Kingdom

Tel: +44-171-728-1000

Fax: +44-171-728

http://www.worldserver.pipex.com/inmarsat/


Program: Inmarsat

Inmarsat 2F1

Inmarsat 2F2

Inmarsat 2F3

Inmarsat 2F4

Inmarsat 3


Inmarsat 2's specifications

Prime contractor	British Aerospace (now MMS)
Platform	Eurostar
Mass at launch	1310 kg with Ariane 1385 kg with Delta
Mass in orbit	BOL: 824 kg
Payload mass	132 kg
Dimension	1.6 x 1.5 x 2.6 m
Solar array	15.23 m span
Stabilization	3 axis
DC power	EOL: equinox: 1156 W, solstice: 1040 W
Payload power	660 W
Design lifetime	10 years
Capacity	250 duplex voice channels

The Inmarsat system has downlinks in L-band that are uplinked in C-band (6 GHz) and uplinks in L-band are downlinked in C-band (4 GHz).

The Inmarsat M standard defines the use on a 10 kg case which cover is the antenna. The uplink frequencies are 1.626-1.660 GHz and 1.525-1.559 GHz for download. Data can be transmitted at 2400 bauds.


Inmarsat 2's L-band (1.6/1.5 GHz)

Main transponders	4
Backup transponders	2
Power	45 W (TWTA)
Bandwidth	total: 18 MHz  carriers: 5 and 22.5 KHz
Coverage	global
EIRP	39 dBW
G/T	12.5 dB/K
Polarization

This capacity is used for communications with the mobiles.


Inmarsat 2's C-band (6.4/3.6 GHz)

Main transponders	1
Backup transponders	1
Power	10 W (TWTA)
Bandwidth	18 MHz
Coverage	global
EIRP	24 dBW
G/T	14.0 dB/K
Polarization

This capacity is used for communications with earth stations.


 Inmarsat 2F1

Also called IOR

General

Designation	20918 / 90093A
Launch date	30 Oct 1990
Country of origin	International
Mission	Telecommunications
Geostationary orbit	see below
Launch vehicle	Delta 2 #200
Location

Begin	End	Position
L: 30 Oct 1991	> Jan 1994	63°E
Jun 1994		64.5°E, inclined

Tel: 873, Telex: 583

Technical data

Specifications

L-band

C-band


 Inmarsat 2F2

Also called AOR-E

General

Designation	21149 / 91018A
Launch date	8 Mar 1991
Country of origin	International
Mission	Telecommunications
Geostationary orbit	15.5°W, inclined
Launch vehicle	Delta 2 #203

Tel: 871, Telex: 581

Technical data

Specifications

L-band

C-band


 Inmarsat 2F3

Also called POR

General

Designation	21814 / 91084B
Launch date	16 Dec 1991
Country of origin	International
Mission	Telecommunications
Geostationary orbit	178°E, inclined
Launch vehicle	Ariane V48

Tel: 872, Telex: 582

Technical data

Specifications

L-band

C-band


 Inmarsat 2F4

Also called AOR-W

General

Designation	21940 / 92021B
Launch date	15 Apr 1992
Country of origin	International
Mission	Telecommunications
Geostationary orbit	see below
Launch vehicle	Ariane V50
Location

Begin	End	Position
L: 15 Apr 1992	end of tests	32°W
end of tests	...	54.5°W, inclined

Tel: 874, Telex: 584

Technical data

Specifications

L-band

C-band


 Inmarsat 3

3F1: 1995, Atlas 2A

3F2: 1996; Atlas 2

3F3: 1996, Ariane

3F4: 1996, Proton

3F5: 1997-98, Ariane

GEO slots: 15.5°W, 34°W, 55°W, 64.5°E, 179.5°E

Specifications

Prime contractor	Lockheed Martin (formerly GE Astro Space)
Platform	GE 4000
Mass at launch	1830-1980 kg
Payload mass	208 kg
Dimension	2.1 x 1.8 x 1.7 m
Solar array	16.7 m
Stabilization	3 axis
DC power	2300 W
Payload power	sunlight: 2138 W, eclipse: 1725 W
Design lifetime	13 years
L-band (1.5/1.6 GHz)

Main transponders
Backup transponders
Power	20 W
Bandwidth	forward: 29 MHz, return: 39 MHz
Coverage & EIRP	Navigation beam: global 5 spots: 47.4 dBW Global: 40.5 dBW
Polarization
C-band (3.6/6.4 GHz)

Main transponders
Backup transponders
Power	15 W
Bandwidth	39 MHz
Coverage	Global
EIRP
Polarization


 Program: Inmarsat P

ICO = Intermediate Circular Orbit

Global mobile telephone system operated by ICO Global Communications, expected to begin service in 1999

Total program value: more than $2 billion. Under a separate agreement, Hughes will invest $93.8 million to become a strategic partner in ICO.

Satellites will be launched by Atlas 2x, Delta 3 an Zenit (none by Ariane)

Overview

Orbit type	MEO
Orbit range	10335 km
Nb of satellites	10 + 2 backup
Nb of planes	2
Inclination	45°
Nb beams per satellite	121
Coverage	12900 km²
Modulation	TDMA
Mobile uplink freq.	1980 - 2010 MHz
Satellite mass	2300 kg
Coverage	Worldwide
Operational date	2000 (planned)
Specifications

Prime contractor	Hughes
Platform
Mass at launch
Mass in orbit
Dimension
Solar array
Stabilization
DC power
Design lifetime

Designed to work with terrestrial GSM


 Program: Insat

Indian National Satellite

Indian telecommunication and meteorology program operated by ISRO

Meteorology mission: image acquisition, distribution of image data and other met info, collection and relay of weather data from data collection platforms (DCPs). Data on upper atmosphere winds and sea surface temperatures, flood and storm early warning, etc.

Contact

ISRO

Antariksh Bhavan, New B.E.L. road, Bangalore 560 084, India

Tel: +91-812-334474

Fax: +91-812-332292


Program: Insat

Insat 1A	Insat 1B	Insat 1C	Insat 1D
Insat 2A	Insat 2B	Insat 2C	Insat 2D
Insat 2E


Insat 1's specifications

Prime contractor	Ford Aerospace
Platform	INSAT
Mass at launch	1152 kg
Mass in orbit	650 kg
Dimension	2.18 x 1.42 x 1.55 m
Solar array	asymmetric pannel, 11.5 m²
Stabilization	3 axis
DC power	1185 W
Design lifetime	7 years


Insat 1's S-band (2.6/5.9 GHz)

Main transponders	2
Backup transponders	1
Power	50 W (TWTA)
Bandwidth
Coverage	India
EIRP	42 dBW
Polarization


Insat 1's C-band

Main transponders	12
Backup transponders
Power	4.5 W (TWTA)
Bandwidth	36 MHz
Coverage	India
EIRP	32 dBW
Polarization


Insat 1's payload

VHRR (Very High Resolution Radiometer)

Wavebands	0.55-0.75 µm (visible) 10.5-12.5 µm (IR)
Resolution	visible: 2.75 km IR: 11 km
Image repeat frequency	30 minutes


Insat 2's specifications

Prime contractor	ISRO/ISAC
Platform	INSAT2
Mass at launch	1906 kg
Mass in orbit	1162 kg
Dimension	1.93 x 1.64 x 1.7 m
Solar array	asymmetric pannel
Stabilization	3 axis
DC power	1400 W
Design lifetime	7 years

Also equipped with 2 single channels for data and search & rescue(Sarsat): 402.75 & 406 MHz


Insat 2's S-band (2.6/5.9 GHz)

Main transponders	2
Backup transponders	1
Power	50 W (TWTA)
Bandwidth	36 MHz
Coverage	India
EIRP	42 dBW
Polarization	LHCP


Insat 2's C-band

Main transponders	18
Backup transponders
Power	4.5 W
Bandwidth	36 MHz
Coverage	India
EIRP	32 dBW
Polarization	H/V linear


Insat 2's payload

VHRR (Very High Resolution Radiometer)

Wave bands	0.55-0.75 µm (visible) 10.5-12.5 µm (IR)
Resolution	visible: 2 km IR: 8 km
Image repeat frequency	30 minutes


 Insat 1A

General

Designation	13129 / 82031A
Launch date	10 Apr 1982
Country of origin	India
Mission	Telecommunications and meteorology
Geostationary orbit	74°E
Launch vehicle	Thor Delta #161
End of life

Cause	Solar panel didn't open out
Technical data

Specifications

S-band

C-band

Payload


 Insat 1B

General

Designation	14318 / 83089B
Launch date	31 Aug 1983
Country of origin	India
Mission	Telecommunications and meteorology
Geostationary orbit	74°E
Launch vehicle	STS 08
End of life

Out of service	yes
Technical data

Specifications

S-band

C-band

Payload


 Insat 1C

General

Designation	19330 / 88063A
Launch date	21 Jul 1988
Country of origin	India
Mission	Telecommunications and meteorology
Geostationary orbit	93.5°E
Launch vehicle	Ariane V24

It had difficulties to open out the solar array. After a power failure, only half its payload is functional.

End of life

Out of service	yes
Technical data

Specifications

S-band

C-band

Payload


 Insat 1D

General

Designation	20643 / 90051A
Launch date	12 Jun 1990
Country of origin	India
Mission	Telecommunications and meteorology
Geostationary orbit	83°E
Launch vehicle	Thor Delta #196

Was damaged when a crane hook fell on it at the launch site and while it was being repared it suffered further damage during the October 1989 California earthquake.

Technical data

Specifications

S-band

C-band

Payload


 Insat 2A

General

Designation	22027 / 92041A
Launch date	9 Jul 1992
Country of origin	India
Mission	Telecommunications and meteorology
Geostationary orbit	74°E
Launch vehicle	Ariane V51
Technical data

Specifications

S-band

C-band

Payload

C-band EIRP coverage (dBW)


Insat 2A's EIRP (C-band)


 Insat 2B

General

Designation	22724 / 93048B
Launch date	22 Jul 1993
Country of origin	India
Mission	Telecommunications and meteorology
Geostationary orbit	93.5°E
Launch vehicle	Ariane V58
Technical data

Specifications

S-band

C-band

Payload


 Insat 2C

General

Designation	23731 / 95067B
Launch date	6 Dec 1995
Country of origin	India
Mission	Telecommunications
Geostationary orbit	93.5°E
Launch vehicle	Ariane V81

Unlike other satellites of the program, Insat 2C is totally devoted to telecommunications and doesn't have any meteorology payload.

Tested at 92.5°E

Technical data

Specifications

Prime contractor	ISRO/ISAC
Platform	INSAT2
Mass at launch	2020 kg
Mass in orbit
Dimension	1.93 x 1.64 x 1.7 m
Solar array	asymmetric pannel
Stabilization	3 axis
DC power	BOL: 1600 W
Design lifetime	10 years

The internal LAM (Liquid Apogee Motor) was built by ISRO with its Indian industrial partners.

S-band (2.6/5.9 GHz)

Main transponders	3
Backup transponders
Power	50 W (TWTA)
Bandwidth	36 MHz
Coverage	India
EIRP	42 dBW
Polarization	LHCP

Aimed at mobile communications

C-band

Main transponders	17 + 6 (wide C-band)
Backup transponders
Power	4.5 W
Bandwidth	36 MHz
Coverage	between the Middle East and southeast Asia
EIRP	32 dBW (2 transponders with 34 dBW)
Polarization	H/V linear

Aimed at TV broadcasting

Ku-band

Main transponders	3
Backup transponders
Power
Bandwidth
Coverage
EIRP
Polarization

Aimed at business communications among India's frou major cities (Delhi, Bombay, Calcutta and Madras)


 Insat 2D

planned to launch in 1996 by Ariane and located at 83°E


 Insat 2E

General

Designation
Launch date	last quarter of 1997
Country of origin	India
Mission	Telecommunications and meteorology
Geostationary orbit
Launch vehicle	Ariane
Launch site
Mass at launch	2500 kg

Intelsat will pay India's Department of Space $100 million over 10 years for the use of 11 transponders. A special capability will be built into the satellite for use by Intelsat in addition to the INSAT system requirement.


 Intasat

General

Designation	07531 / 74089C
Launch date	15 Nov 1974
Country of origin	Spain
Mission	Scientific: ionosphere study
Perigee/Apogee	1441/1455 km
Inclination	101.9°
Period	114.8 min
Launch vehicle	Thor Delta #104
Mass at launch	24.5 kg

Studies the ionosphere's density and its movement throughout the year.


 Program: Intelsat

INTernational TELecommunication SATellite

Intelsat was created by 11 states (leaded by the United States) on 24 Aug 1964. The Comsat (controled by the US federal government) was created to manage the system because the US had 61% of the voting part. In 1979 the structure changed so that each member can't possess more that 40% of the voting parts.

Since 1966, all the continents are covered by Intelsat and nowadays numerous services are offered. Intelsat counts 134 members.

Contact

Intelsat

3400 International drive NW, Box 63, Washington DC, 20008, USA

Tel: +1-202-944-7500

Fax: +1-202-944-7890

http://www.intelsat.int:8080/


Program: Intelsat

Intelsat 101
Intelsat 201	Intelsat 202	Intelsat 203	Intelsat 204
Intelsat 301	Intelsat 302	Intelsat 303	Intelsat 304
Intelsat 305	Intelsat 306	Intelsat 307	Intelsat 308
Intelsat 401	Intelsat 402	Intelsat 403	Intelsat 404
Intelsat 405	Intelsat 406	Intelsat 407	Intelsat 408
Intelsat 4A01	Intelsat 4A02	Intelsat 4A03	Intelsat 4A04
Intelsat 4A05	Intelsat 4A06
Intelsat 501	Intelsat 502	Intelsat 503	Intelsat 504
Intelsat 505	Intelsat 506	Intelsat 507	Intelsat 508
Intelsat 509	Intelsat 510	Intelsat 511	Intelsat 512
Intelsat 513	Intelsat 514	Intelsat 515
Intelsat 601	Intelsat 602	Intelsat 603	Intelsat 604
Intelsat 605		Intelsat K
Intelsat 701	Intelsat 702	Intelsat 703	Intelsat 704
Intelsat 705	Intelsat 706	Intelsat 707	Intelsat 708
Intelsat 709
Intelsat 801	Intelsat 802	Intelsat 803	Intelsat 804
Intelsat 805	Intelsat 806


Intelsat 2's specifications

Mass at launch	162 kg
Mass in orbit	86 kg
Length
Width	1.42 m
Height	0.67 m
Stabilization	Spin stabilised
DC power	BOL: 83 W EOL: 75 W
Design lifetime	3 years

The antenna platform didn't counter rotate thus most of the power didn't reach the Earth. 360° omnidirectional antenna!


Intelsat 2's C-band

Main transponders	1
Power	18 W
Bandwidth	125 MHz
EIRP	15.5 dBW
Capacity	240 phone circuits or 1 TV channel

Allows multiple access


Intelsat 3's specifications

Mass at launch	293 kg
Mass in orbit	151 kg
Length
Width	1.41 m
Height	2.02 m
Stabilization	spin stabilized
DC power	BOL: 160 W EOL: 125 W
Design lifetime	5 years


Intelsat 3's C-band

Main transponders	2
Power	11 W
Bandwidth	225 MHz
EIRP	23 dBW
Capacity	1500 phone circuits and 2 TV channels


Intelsat 4's specifications

Mass at launch	1415 kg
Mass in orbit	700 kg
Length
Width	2.38 m
Height	5.28 m
Stabilization	spin stabilized
DC power	BOL: 600 W EOL: 400 W
Design lifetime	7 years


Intelsat 4's C-band

Main transponders	12
Power	6 W
Bandwidth	36 MHz
Coverage and EIRP	Global (4 beams): 22.5 dBW 2 spot beams: 33.7 dBW
Capacity	4000 phone circuits and 2 TV channels


Intelsat 4A's specifications

Mass at launch	1515 kg
Mass in orbit	793 kg
Length
Width	2.38 m
Height	6.93 m
Stabilisation	Spin stabilized (60 rpm)
DC power	BOL: 700 W EOL: 500 W
Design lifetime	7 years


Intelsat 4A's C-band

Main transponders	20
Power	6.5 W or 8 W?
Bandwidth	36 MHz
Coverage and EIRP	Global: 22 dBW Hemispheric (2 beams): 26 dBW Spot beam: 29 dBW
Capacity	6000 phone circuits and 2 TV channels

First generation with separated hemispheric beams which allowed the reuse of same frequencies on the 2 antennas.


Intelsat 5's specifications

Prime contractor	Ford Aerospace
Platform	Intelsat 5
Mass at launch	1900 kg
Mass in orbit	1040 kg
Payload mass	233.5 kg: transponders: 174.6 kg, antennas: 58.9 kg
Dimension	1.66 x 2 x 1.77 m (with tower: 6.4 m)
Solar array	15.58 m span
DC power	BOL: 1800 W EOL: equinox: 1400 W, solstice: 1288 W
Payload power	753.8 W
Stabilization	3 axis
Design lifetime	7 years
Capacity	12000 phone circuits and 2 TV channels


Intelsat 5's L-band

Main transponders	2
Backup transponders
Power
Bandwidth
Coverage
EIRP	33 dBW
Polarization

Only on 505 to 509. Those transponders are leased to Inmarsat


Intelsat 5's C-band

Main transponders	21
Backup transponders
Power	Global, hemispheric and zone beams: 8.5 W (TWTA) Spot beam: 4.5 W
Bandwidth	36 and 72 MHz
Coverage and EIRP	Global: 23.5 dBW Hemispheric and zone: 29 dBW
Polarization	circular R/L
Beacons	3.9475 & 3.9525 GHz

First generation with orthogonal polarizations. Together with the use of 2 separated hemispheric beams more frequency space could be saved.


Intelsat 5's Ku-band

Main transponders	6
Backup transponders	4
Power	10 W (TWTA)
Bandwidth	2 transponders of 72 MHz 2 transponders of 241 MHz
Coverage	2 spot beams
EIRP	West: 44.4 dBW East: 41.1 dBW
Polarization	linear
Beacons	11.198 & 11.452 GHz


Intelsat 5A's specifications

Prime contractor	Ford Aerospace
Platform	Intelsat 5
Mass at launch	1900 kg
Mass in orbit	1040 kg
Payload mass	262.7 kg: transponders: 187.2 kg, antennas: 58.9 kg
Dimension	1.66 x 2 x 1.77 m
Solar array	15.58 m span
DC power	BOL: 1800 W EOL: equinox: 1427 W, solstice: 1351 W
Payload power	875.3 W
Stabilization	3 axis
Design lifetime	7 years
Phone circuits	15000
Reserved TV channels	2


Intelsat 5A's C-band

Main transponders	32
Backup transponders	12
Power	Global, hemispheric and zone beams: 8.5 W (TWTA) Spot beams: 4.5 W
Bandwidth	36 and 72 MHz
Coverage and EIRP	Global: 23.5 dBW Hemispheric and zone beams: 29 dBW Spot beam: 32.5 dBW
Polarization	circular R/L
Beacons	3.9475, 3.948, 3.952 & 3.9525 GHz


Intelsat 5A's Ku-band

Main transponders	6
Backup transponders	4
Power	10 W (TWTA)
Bandwidth	2 transponders of 72 MHz 2 transponders of 241 MHz
Coverage	2 spot beams
EIRP	West: 44.4 dBW East: 41.1 dBW
Polarization	linear
Beacons	11.198 & 11.452 GHz


Intelsat 6's specifications

Prime contractor	Hughes
Platform	Intelsat 6 (HS389)
Mass at launch	~4300 kg
Mass in orbit	2560 kg
Payload mass	660 kg: transponders: 332 kg, antennas: 330 kg
Diameter	3.63 m
Height	6.4 m (11.84 m stowed)
DC power	BOL: 2600 W EOL: equinox: 2204 W, solstice: 2083 W
Payload power	~1600 W
Stabilization	Spin stabilized
Design lifetime	13 years
Phone circuits	24000 (120000 with DCME)
Reserved TV channels	3

2 telemetry and remote control antennas.


Intelsat 6's C-band

Main transponders	6+32
Backup transponders	2+10
Power	(6+2) transponders of 16 W (TWTA) (32+10) transponders of 10 W (SSPA)
Bandwidth	36 and 72 MHz
Coverage and EIRP	Global beam: 26.5 dBW Hemispheric: 29 dBW Zone: 31 dBW
Polarization	circular R/L
Beacons	3.9475, 3.948, 3.952 & 3.9525 GHz


Intelsat 6's Ku-band

Main transponders	8+2
Backup transponders	3+1
Power	(8+3) transponders of 20 W (TWTA) (2+1) transponders of 40 W (TWTA)
Bandwidth	36 MHz
Coverage and EIRP	West & East spots: 44.7 dBW
Polarization	linear
Beacons	11.198 & 11.452 GHz


Intelsat 7's specifications

Prime contractor	Space Systems/Loral
Platform	Intelsat 7 (based on Ford FS 1300 and Aerospatiale Spacebus 2000)
Mass at launch	3750 kg
Mass in orbit	1800 kg
Dry mass	1500 kg
Payload mass	446 kg: transponders: 338kg, antennas: 108 kg
Dimension	2.45 x 2.2 x 2.7 m
Solar array	21.8 m span
DC power	EOL: equinox: 3968 W, solstice: 3650 W
Payload power	2580 W
Stabilization	3 axis
Design lifetime	10-15 years
Phone circuits	18000 (90000 with DCME)
Reserved TV channels	3

Cross-strapping: uplink in C-band and downlink in Ku-band (701, 702, 703, 704, 705 & 709)


Intelsat 7's C-band

Main transponders	26
Backup transponders
Power	10, 16, 20 & 30 W
Bandwidth	8 transponders of 36 MHz 2 transponders of 41 MHz 16 transponders of 72 MHz
Coverage and EIRP	Global beam: 26/29 dBW Hemispheric beam: 33 dBW (2x36 MHz & 8x72 MHz) Zone beam: 33 dBW (2x36 MHz & 8x72 MHz) Spot beam: 33.3/36.3 dBW
Polarization	circular R/L

Four 36 MHz and the two 41 MHz transponders are either in global or in spot configuration. The two 41 MHz transponders are 3 dBW stronger than the others.


Intelsat 7's Ku-band

Main transponders	10
Backup transponders
Power	5 transponders of 35 W 5 transponders of 50 W
Bandwidth	6 transponders of 72 MHz 4 transponders of 112 MHz
Coverage and EIRP	Spot 1: 45.4 dBW Spot 2: 44.5 dBW Spot 3: 46 dBW (the nominal power can be increased)
Polarization	linear

Five transponders max per spot. Spot 1 is V, spot 2 is H and spot 3 is either H or V depending on the spot (1 or 2) it belonged to (only 701, 702 & 703 have this polarization limitation, on the others the polarization can be choosen).

The downlink can be switched to 10.95-11.20 GHz, 11.45-11.70 GHz, 11.70-11.95 GHz & 12.50-12.75 GHz


Intelsat 7A's specifications

Prime contractor	Space Systems/Loral
Platform	FS 1300
Mass at launch	4500 kg
Payload mass	525 kg: transponders: 412 kg, antennas: 113 kg
Dimension	2.7 x 2.2 x 2.45 m
Solar array	25.7 m span
DC power	EOL: equinox: 5326 W, solstice: 4884 W
Payload power	3612 W
Stabilization	3 axis
Design lifetime	10-15 years
Phone circuits	22500 (112500 with DCME)
Reserved TV channels	3

(706, 707 & 708)


Intelsat 7A's C-band

Main transponders	26
Backup transponders
Power	10, 20 & 30 W
Bandwidth	10 transponders of 36 MHz 16 transponders of 72 MHz
Coverage and EIRP	Global beam (36 MHz): 29 dBW Hemispheric beam (8x72 MHz & 2x36 MHz): 33 dBW Zone beam (8x72 MHz & 2x36 MHz): 33 dBW Spot beam (36 MHz): 36.1 dBW
Polarization	circular R/L

A total of 6 transponder are switched either to global or to spot beam.


Intelsat 7A's Ku-band

Main transponders	14
Backup transponders
Power	5 transponders of 49 W 5 transponders of 73 W
Bandwidth	6 transponders of 72 MHz 8 transponders of 112 MHz
Coverage and EIRP	Spot 1: 47 dBW Spot 2: 47 dBW Spot 3: 42.8 dBW (the nominal power can be increased)
Polarization	linear

Five transponders max per spot.


Intelsat 8's specifications

Prime contractor	Lockheed Martin Astro Space
Platform	GE 7000
Mass at launch	3700 kg
Stabilization	3 axis
Design lifetime	14-18 years
Phone circuits	22500 (112500 with DCME)
Reserved TV channels	3

4 satellites ordered (801-804)


Intelsat 8's C-band

Main transponders	32
Backup transponders
Power	20-30 W
Bandwidth	36 and 72 MHz
Coverage & EIRP	Global: 29 dBW Hemispheric: 36 dBW Zone: 36 dBW
Polarization


Intelsat 8's Ku-band

Main transponders	9 to 12
Backup transponders
Power	50 W
Bandwidth	72 and 112 MHz
Coverage & EIRP	West & East spots: 47 dBW
Polarization

Equipped with steerable Ku spots for VSAT.


Intelsat 8A's specifications

Prime contractor	LM Astro Space
Design lifetime	14-18 years

2 satellites ordered (805-806), will be specifically customized


page intentionally left blank


 Intelsat 101

Also called Early Bird

General

Designation	01317 / 65028A
Launch date	6 Apr 1965
Country of origin	International
Mission	Telecommunications
Geostationary orbit	35752/35823 km, 27.5°W
Launch vehicle	Thor Delta #30
End of life

Out of service	May 1970
Technical data

Specifications

Prime contractor	Hughes
Mass at launch	68 kg
Mass in orbit	38.5 kg
Length
Width	0.72 m
Height	0.59 m
Stabilization	spin stabilized (120 rpm)
DC power	BOL: 45 W EOL: 33 W
Design lifetime	1.5 year

The antenna platform didn't counter rotate thus most of the power didn't reach the Earth. The antenna was 360° omnidirectional!

C-band

Main transponders	2
Power	6 W
Bandwidth	25 MHz
EIRP	11.5 dBW
Capacity	240 phone circuits or 1 TV channel

Didn't allow multiple access: the European stations: Pleumeur-Bodou (France), Goonhilly Downs (UK), Raisting (Germany) and Fucino (Italy) used to operated 1 week per month!


 Intelsat 201

General

Designation	02514 / 66096A
Launch date	26 Oct 1966
Country of origin	International
Mission	Telecommunications
Geostationary orbit	n/a (3424 km x 37531 km x 17.2° x 730 min)
Launch vehicle	Thor Delta #42
End of life

Out of service	26 Oct 1966
Cause	Remained on the transfert (the apogee kick motor failed)
Technical data

Specifications

C-band


 Intelsat 202

General

Designation	02639 / 67001A
Launch date	11 Jan 1967
Country of origin	International
Mission	Telecommunications
Geostationary orbit	Pacific Ocean Region
Launch vehicle	Thor Delta #44
End of life

Out of service	yes
Technical data

Specifications

C-band


 Intelsat 203

General

Designation	02717 / 67026A
Launch date	23 Mar 1967
Country of origin	International
Mission	Telecommunications
Geostationary orbit	4°W
Launch vehicle	Thor Delta #47
End of life

Out of service	yes
Technical data

Specifications

C-band


 Intelsat 204

General

Designation	02969 / 67094A
Launch date	28 Sep 1967
Country of origin	International
Mission	Telecommunications
Geostationary orbit	179°E
Launch vehicle	Thor Delta #52
End of life

Out of service	yes
Technical data

Specifications

C-band


 Intelsat 301

End of life

Out of service	18 Sep 1968
Cause	Launch failure (Thor Delta #59)
Technical data

Specifications

C-band


 Intelsat 302

General

Designation	03623 / 68116A
Launch date	19 Dec 1968
Country of origin	International
Mission	Telecommunications
Geostationary orbit	31°W
Launch vehicle	Thor Delta #63
End of life

Out of service	yes
Technical data

Specifications

C-band


 Intelsat 303

General

Designation	03674 / 69011A
Launch date	6 Feb 1969
Country of origin	International
Mission	Telecommunications
Geostationary orbit	57°E
Launch vehicle	Thor Delta #66
End of life

Out of service	yes
Technical data

Specifications

C-band


 Intelsat 304

General

Designation	03947 / 69045A
Launch date	22 May 1969
Country of origin	International
Mission	Telecommunications
Geostationary orbit	174°E
Launch vehicle	Thor Delta #68
End of life

Out of service	yes
Technical data

Specifications

C-band


 Intelsat 305

General

Designation	04051 / 69064A
Launch date	26 Jul 1969
Country of origin	International
Mission	Telecommunications
Geostationary orbit	n/a
Launch vehicle	Thor Delta #71
End of life

Out of service	26 Jul 1969
Cause	Placed on a wrong orbit (271 km x 5397 km x 30.7° x 176.6 min)
Decay	14 Oct 1988
Technical data

Specifications

C-band


 Intelsat 306

General

Designation	04297 / 70003A
Launch date	15 Jan 1970
Country of origin	International
Mission	Telecommunications
Geostationary orbit	27.5°W
Launch vehicle	Thor Delta #75
End of life

Out of service	yes
Technical data

Specifications

C-band


 Intelsat 307

General

Designation	04376 / 70032A
Launch date	23 Apr 1970
Country of origin	International
Mission	Telecommunications
Geostationary orbit	24.5°W
Launch vehicle	Thor Delta #78
End of life

Out of service	yes
Technical data

Specifications

C-band


 Intelsat 308

General

Designation	04478 / 70055A
Launch date	23 Jul 1970
Country of origin	International
Mission	Telecommunications
Geostationary orbit
Launch vehicle	Thor Delta #79
End of life

Out of service	yes
Technical data

Specifications

C-band


 Intelsat 401

General

Designation	07815 / 75042A
Launch date	22 May 1975
Country of origin	International
Mission	Telecommunications
Geostationary orbit	18.5°W
Launch vehicle	Atlas Centaur
Launch site	Cape Canaveral
End of life

Out of service	yes
Technical data

Specifications

C-band


 Intelsat 402

General

Designation	04881 / 71006A
Launch date	26 Jan 1971
Country of origin	International
Mission	Telecommunications
Geostationary orbit	19.5°W
Launch vehicle	Atlas Centaur
Launch site	Cape Canaveral
End of life

Out of service	yes
Technical data

Specifications

C-band


 Intelsat 403

General

Designation	05709 / 71116A
Launch date	20 Dec 1971
Country of origin	International
Mission	Telecommunications
Geostationary orbit	21.5°W
Launch vehicle	Atlas Centaur
Launch site	Cape Canaveral
End of life

Out of service	yes
Technical data

Specifications

C-band


 Intelsat 404

General

Designation	05775 / 72003A
Launch date	23 Jan 1972
Country of origin	International
Mission	Telecommunications
Geostationary orbit	179°E
Launch vehicle	Atlas Centaur
Launch site	Cape Canaveral
End of life

Out of service	yes
Technical data

Specifications

C-band


 Intelsat 405

General

Designation	06052 / 72041A
Launch date	13 Jun 1972
Country of origin	International
Mission	Telecommunications
Geostationary orbit	57°E
Launch vehicle	Atlas Centaur
Launch site	Cape Canaveral
End of life

Out of service	yes
Technical data

Specifications

C-band


 Intelsat 406

End of life

Out of service	20 Feb 1975
Cause	Launch failure (Atlas Centaur)
Technical data

Specifications

C-band


 Intelsat 407

General

Designation	06796 / 73058A
Launch date	23 Aug 1973
Country of origin	International
Mission	Telecommunications
Geostationary orbit	1°W
Launch vehicle	Atlas Centaur
Launch site	Cape Canaveral
End of life

Out of service	yes
Technical data

Specifications

C-band


 Intelsat 408

General

Designation	07544 / 74093A
Launch date	21 Nov 1974
Country of origin	International
Mission	Telecommunications
Geostationary orbit	174°E
Launch vehicle	Atlas Centaur
Launch site	Cape Canaveral
End of life

Out of service	yes
Technical data

Specifications

C-band


 Intelsat 4A01

General

Designation	08330 / 75091A
Launch date	26 Sep 1975
Country of origin	International
Mission	Telecommunications
Geostationary orbit	24.5°W
Launch vehicle	Atlas Centaur
Launch site	Cape Canaveral
End of life

Out of service	yes
Technical data

Specifications

C-band


 Intelsat 4A02

General

Designation	08620 / 76010A
Launch date	29 Jan 1976
Country of origin	International
Mission	Telecommunications
Geostationary orbit	27.5°W
Launch vehicle	Atlas Centaur
Launch site	Cape Canaveral
End of life

Out of service	yes
Technical data

Specifications

C-band


 Intelsat 4A03

General

Designation	10557 / 78002A
Launch date	7 Jan 1978
Country of origin	International
Mission	Telecommunications
Geostationary orbit	60°E
Launch vehicle	Atlas Centaur
Launch site	Cape Canaveral
End of life

Out of service	yes
Technical data

Specifications

C-band


 Intelsat 4A04

General

Designation	10024 / 77041A
Launch date	26 May 1977
Country of origin	International
Mission	Telecommunications
Geostationary orbit	34.5°W
Launch vehicle	Atlas Centaur
Launch site	Cape Canaveral
End of life

Out of service	yes
Technical data

Specifications

C-band


 Intelsat 4A05

End of life

Out of service	29 Sep 1977
Cause	Launch failure (Atlas Centaur): explosion after 55 s
Technical data

Specifications

C-band


 Intelsat 4A06

General

Designation	10778 / 78035A
Launch date	31 Mar 1978
Country of origin	International
Mission	Telecommunications
Geostationary orbit	63°E
Launch vehicle	Atlas Centaur
Launch site	Cape Canaveral
End of life

Out of service	yes
Technical data

Specifications

C-band


 Intelsat 501

General

Designation	12474 / 81050A
Launch date	23 May 1981
Country of origin	International
Mission	Telecommunications
Geostationary orbit	see below
Launch vehicle	Atlas Centaur
Launch site	Cape Canaveral
Location

Begin	End	Position
L: 23 May 1981
May 1988		went inclined
late 1991	late 1991	177°W, inclined
Oct 1992	Jan 1996	91.5°E, inclined (left to leave the slot to Measat 1)
late Feb 1996		72°E, inclined
Technical data

Specifications

C-band

Ku-band


 Intelsat 502

General

Designation	12089 / 80098A
Launch date	6 Dec 1980
Country of origin	International
Mission	Telecommunications
Geostationary orbit	see below
Launch vehicle	Atlas Centaur
Launch site	Cape Canaveral
Location

Begin	End	Position
L: 6 Dec 1980
Dec 1988		went inclined
Jan 1991	Jan 1991	1°W, inclined
Feb 1992	Oct 1994	21.5°W, inclined
Oct 1994		40.5°W, inclined
Technical data

Specifications

C-band

Ku-band

When in 21.5°W, the antenna's platform was rotated in December 1992 to enable a direct link between Somalia and the US. The Eastern spot was pointed to Somalia.

EIRP coverage (dBW)

C-band

Ku-band


Intelsat 502's C-band EIRP


Intelsat 502's Ku-band EIRP


 Intelsat 503

General

Designation	12994 / 81119A
Launch date	15 Dec 1981
Country of origin	International
Mission	Telecommunications
Geostationary	see below
Launch vehicle	Atlas Centaur
Launch site	Cape Canaveral
Location

Begin	End	Position
L: 15 Dec 1981
May 1989		went inclined
1 Jan 1991	late 1991	174°E, inclined
Oct 1992	Aug 1995	177°W, inclined
Aug 1995	mid-Dec 1995	drifting West
mid-Dec 1995		157°W, inclined
Technical data

Specifications

C-band

Ku-band


 Intelsat 504

General

Designation	13083 / 82017A
Launch date	5 Mar 1982
Country of origin	International
Mission	Telecommunications
Geostationary orbit	see below
Launch vehicle	Atlas Centaur
Launch site	Cape Canaveral
Location

Begin	End	Position
L: 5 Mar 1982
Apr 1989		went inclined
Jan 1991	Oct 1992	34.5°W, inclined
July 1993	Sep 1993	32°W, inclined
Dec 1993	Jan 1994	40.5°W, inclined
May 1994	May 1995	31.5°W, inclined
Jul 1995	Nov 1995	29.4°W, inclined
End of life

Out of service	late Nov 1995
Cause	end of life: deorbited
Technical data

Specifications

C-band

Ku-band


 Intelsat 505

Also called Intelsat MCS-A

General

Designation	13595 / 82097A
Launch date	28 Sep 1982
Country of origin	International
Mission	Telecommunications
Geostationary orbit	see below
Launch vehicle	Atlas Centaur
Launch site	Cape Canaveral
Location

Begin	End	Position
L: 28 Sep 1982
Dec 1989		went inclined
Jan 1991	end of 1991	63°E, inclined
Feb 1992	Aug 1994	66°E, inclined
Nov 1994		65°E, inclined
Technical data

Specifications

L-band

C-band

Ku-band


 Intelsat 506

Also called Intelsat MCS-B

General

Designation	14077 / 83047A
Launch date	19 May 1983
Country of origin	International
Mission	Telecommunications
Geostationary orbit	see below
Launch vehicle	Atlas Centaur
Launch site	Cape Canaveral
Location

Begin	End	Position
L: 19 May 1983
Jan 1991		went inclined
Jan 1991	Feb 1992	18.5°W, inclined
Jul 1992	Jul (Sep?) 1992	34.5°W, inclined
Oct 1992	May 1995	50°W, inclined
Jun 1995		31.4°W, inclined
Technical data

Specifications

L-band

C-band

Ku-band

EIRP coverage (dBW)

C-band

Ku-band


Intelsat 506's C-band EIRP


Intelsat 506's Ku-band EIRP


 Intelsat 507

Also called Intelsat MCS-C

General

Designation	14421 / 83105A
Launch date	19 Oct 1983
Country of origin	International
Mission	Telecommunications
Geostationary orbit	see below
Launch vehicle	Ariane L07

First Intelsat launched by a non US vehicle.

Location

Begin	End	Position
L: 19 Oct 1983
Aug 1990		went inclined
Mar 1991	Mar 1991	66°E, inclined
end of 1991	Mar 1995	57°E, inclined
Apr 1995		47°E, inclined
Technical data

Specifications

L-band

C-band

Ku-band

EIRP coverage (dBW)

C-band

Ku-band


Intelsat 507's C-band EIRP


Intelsat 507's Ku-band EIRP


 Intelsat 508

Also called "PolySat" and Intelsat MCS-D

General

Designation	14786 / 84023A
Launch date	5 Mar 1984
Country of origin	International
Mission	Telecommunications
Geostationary orbit	180°E
Launch vehicle	Ariane L08
End of life

Out of service	yes
Technical data

Specifications

L-band

C-band

Ku-band


 Intelsat 509

General

Designation	15034 / 84057A
Launch date	9 Jun 1984
Country of origin	International
Mission	Telecommunications
Geostationary orbit	n/a
Launch vehicle	Atlas Centaur
Launch site	Cape Canaveral
End of life

Out of service	9 Jun 1984
Cause	Launcher partial failure
Decay	24 Oct 1984
Technical data

Specifications

L-band

C-band

Ku-band


 Intelsat 510

General

Designation	15629 / 85025A
Launch date	22 Mar 1985
Country of origin	International
Mission	Telecommunications
Geostationary orbit	see below
Launch vehicle	Atlas Centaur
Launch site	Cape Canaveral
Location

Begin	End	Position
L: 22 mar 1984		174°E
Aug 1992		went inclined
Feb 1995	Mar 1995	66°E, inclined
Apr 1995		57°E, inclined
Technical data

Specifications

C-band

Ku-band

EIRP coverage (dBW)

C-band

Ku-band


Intelsat 510's C-band EIRP


Intelsat 510's Ku-band EIRP


 Intelsat 511

General

Designation	15873 / 85055A
Launch date	30 Jun 1985
Country of origin	International
Mission	Telecommunications
Geostationary orbit	see below
Launch vehicle	Atlas Centaur
Launch site	Cape Canaveral

Transmits the phone communications in the Pacific

Location

Begin	End	Position
L: 30 Jun 1985
Jan 1991	Jan 1991	27.5°W
late 1991	Sep 1992	63°E
Oct 1992	Feb 1993	177°E
Feb 1993	Nov 1994	177°E, went inclined
Feb 1995		180°E, inclined
Technical data

Specifications

C-band

Ku-band

EIRP coverage (dBW)

C-band

Ku-band


Intelsat 511's C-band EIRP


Intelsat 511's Ku-band EIRP


 Intelsat 512

General

Designation	16101 / 85087A
Launch date	29 Sep 1985
Country of origin	International
Mission	Telecommunications
Geostationary orbit	see below
Launch vehicle	Atlas Centaur
Launch site	Cape Canaveral
Location

Begin	End	Position
L: 29 Sep 1985
Jan 1991	Jan 1991	34.5°W
Mar 1991	Jun 1994	1°W
Jun 1994	Aug 1994	1°W, went inclined
Sep 1994		21.5°W, inclined
Technical data

Specifications

C-band

Ku-band

EIRP coverage (dBW)

C-band

Ku-band

Ku-band used: 11.01-11.59 GHz


Intelsat 512's C-band EIRP


Intelsat 512's Ku-band EIRP


 Intelsat 513

General

Designation	19121 / 88040A
Launch date	17 May 1988
Country of origin	International
Mission	Telecommunications
Geostationary orbit	see below
Launch vehicle	Ariane V22
Location

Begin	End	Position
L: 17 May 1988	Jul 1995	53°W
Aug 1995		177°W, inclined (from Aug 1995 on)
Technical data

Specifications

C-band

Ku-band

Would have transponders in Ku's Telecom band?


 Intelsat 514

End of life

Out of service	30 May 1986
Cause	Explosion of Ariane V18
Technical data

Specifications

C-band

Ku-band


 Intelsat 515

General

Designation	19772 / 89006A
Launch date	27 Jan 1989
Country of origin	International
Mission	Telecommunications
Geostationary orbit	see below
Launch vehicle	Ariane V28
Location

Begin	End	Position
L: 27 Jan 1989
Jan 1991	Feb 1992	60°E
Apr 1992		18°W

Should go inclined (North-South stabilization shutdown) in May 1997

Technical data

Specifications

C-band

Ku-band

EIRP coverage (dBW)

C-band

Ku-band


Intelsat 515's C-band EIRP


Intelsat 515's Ku-band EIRP


 Intelsat 601

General

Designation	21765 / 91075A
Launch date	29 Oct 1991
Country of origin	International
Mission	Telecommunications
Geostationary orbit	see below
Launch vehicle	Ariane V47
Location

Begin	End	Position
L: 29 Oct 1991
late 1991	...	27.5°W
Technical data

Specifications

C-band

Ku-band

EIRP coverage (dBW)

C-band

Ku-band Eastern spot

Ku-band Western spot


Intelsat 601's C-band EIRP


Intelsat 601's EIRP (Ku-band Eastern spot)


Intelsat 601's EIRP (Ku-band Western spot)


 Intelsat 602

General

Designation	20315 / 89087A
Launch date	27 Oct 1989
Country of origin	International
Mission	Telecommunications
Geostationary orbit	see below
Launch vehicle	Ariane V34
Location

Begin	End	Position
L: 27 Oct 1989
Jan 1991	Feb 1992	24.5°W
Apr 1992	Apr 1992	60°E
Oct 1992	...	63°E
Technical data

Specifications

C-band

Ku-band

EIRP coverage (dBW)

C-band

Ku-band


Intelsat 602's C-band EIRP


Intelsat 602's Ku-band EIRP


 Intelsat 603

General

Designation	20523 / 90021A
Launch date	14 Mar 1990
Country of origin	International
Mission	Telecommunications
Geostationary orbit	34.5°W
Launch vehicle	Titan 3
Launch site	Cape Canaveral

The satellite was repared (apogee kick motor changed) by STS 49 in May 1992.

Technical data

Specifications

C-band

Ku-band

EIRP coverage (dBW)

C-band

Ku-band


Intelsat 603's C-band EIRP


Intelsat 603's Ku-band EIRP


 Intelsat 604

General

Designation	20667 / 90056A
Launch date	23 Jun 1990
Country of origin	International
Mission	Telecommunications
Geostationary orbit	see below
Launch vehicle	Titan 3
Launch site	Cape Canaveral
Location

Begin	End	Position
L: 23 Jun 1990
Jan 1991	Feb 1992	27.5°W
Oct 1992	...	60°E
Technical data

Specifications

C-band

Ku-band

EIRP coverage (dBW)

C-band

Ku-band

Ku-band used: 10.97-11.6 GHz


Intelsat 604's C-band EIRP


Intelsat 604's Ku-band EIRP


 Intelsat 605

General

Designation	21653 / 91055A
Launch date	14 Aug 1991
Country of origin	International
Mission	Telecommunications
Geostationary orbit	see below
Launch vehicle	Ariane V45
Location

Begin	End	Position
L: 14 Aug 1991
late 1991	late 1991	21.5°W
Jul 1992	...	24.5°W
Technical data

Specifications

C-band

Ku-band

EIRP coverage (dBW)

C-band

Ku-band


Intelsat 605's C-band EIRP


Intelsat 605's Ku-band EIRP


 Intelsat K

General

Designation	21989 / 92032A
Launch date	10 Jun 1992
Country of origin	International
Mission	Telecommunications
Geostationary orbit	21.5°W
Launch vehicle	Atlas Centaur

First Intelsat Ku-band only satellite for TV channels transmission. This satellite is a modified Satcom bought to respond to urgent needs over Atlantic.

Technical data

EIRP coverage (dBW)

EIRP coverage to America (dBW)

EIRP coverage to Europe (dBW)

Specifications

Prime contractor	GE Astro Space
Platform	GE 5000
Mass at launch	2836 kg
Mass in orbit	1547 kg
Dimension	2.84 x 2.26 x 2.18 m
Solar array	31.2 m span
Stabilization	3 axis
DC power	BOL: 4800 W EOL: equinox: 3639 W
Design lifetime	10 years
Ku-band

Main transponders	16
Backup transponders
Power	62.5 W (TWTA)
Bandwidth	54 MHz
Coverage and EIRP	United States: 47 dBW Europe: 47 dBW South America: 45 dBW
Polarization	linear
Transponder frequency chart (GHz)

Transponder	Polarization	Frequency	Coverage
1	V	11.735	To America
2	H/V	11.795	To America
3	H/V	11.855	To America
4	H/V	11.915	To America
5	H/V	11.485	Switchable
6	V	11.545	Switchable
7	V	11.605	Switchable
8	H/V	11.665	Switchable
9	H/V	12.536	To Europe
10	H/V	12.595	To Europe
11	H/V	12.655	To Europe
12	H/V	12.715	To Europe


Intelsat K's Ku-band to America


Intelsat K's EIRP to Europe


 Intelsat 701

General

Designation	22871 / 93066A
Launch date	22 Oct 1993
Country of origin	International
Mission	Telecommunications
Geostationary orbit	174°E
Launch vehicle	Ariane V60

Cost: $103 million

Technical data

Specifications

C-band

Ku-band

EIRP coverage (dBW)

C-band

Ku-band

Has 4 Ku-band spot beams


Intelsat 701's C-band EIRP


Intelsat 701's Ku-band EIRP


 Intelsat 702

General

Designation	23124 / 94034A
Launch date	17 Jun 1994
Country of origin	International
Mission	Telecommunications
Geostationary orbit	see below
Launch vehicle	Ariane V64
Location

Begin	End	Position
L: 17 Jun 1994	end of tests	37.75°W
end of tests	...	1°W
Technical data

Specifications

C-band

Ku-band

EIRP coverage (dBW)

C-band

Ku-band

C-band transponder frequency chart (GHz)

Warning: this chart is only a compilation made from observations! It is partial and not reliable.

LHCP Zone 1	LHCP Zone 2	Downlink	RHCP Hemi 1	RHCP Hemi 2	Bandwith (MHz)
51A	x	x	21A	x
51	x	3.7425	21	x	72 MHz
51B	x	x	21B	x
52A	x	x	22A	x
52	x	3.825	22	x	72 MHz
52B	x	3.840	22B	x
53A	x	x	23A	x
53	x	3.905	23	x	72 MHz
53B	x	x	23B	x
54A	x	x	24A	x
54	x	3.995	24	x	72 MHz
54B	x	4.022	24B	x
55	x	4.135	25	x	36 MHz
LHCP Global or Spot		Downlink		RHCP Global or Spot
		3.925
x		4.055		x	36 MHz
x		4.095		x	36 MHz
x		4.1775		38	41 MHz
Ku-band

Transponders 61, 62, 63, 71, 72 and 73 can be swiched all together on either FSS, DBS or Telecom Ku-band.

Spot 1 is composed of the vertical transponders whereas spot 2 is composed of horizontal transponders. These transponders (5 max) can be moved to spot 3 keeping their original polarization.

Ku-band transponder frequency chart (GHz)

Horizontal	FSS	DBS	Telecom	Vertical
61A	10.971	11.726	12.526	71A
61	10.9925	11.7475	12.5475	71	72 MHz
61B	11.014	11.769	12.569	71B
62A	11.055	11.810	12.610	72A
62	11.075	11.830	12.630	72	72 MHz
62B	11.095	11.850	12.650	72B
63A	11.133	11.877	12.677	73A
63	11.155	11.910	12.710	73	72 MHz
63B	11.178	11.943	12.743	73B
68A	11.478	n/a	n/a	78A
68/68B	11.514	n/a	n/a	78/78B	112 MHz
68C	11.555	n/a	n/a	78C
69A	11.597	n/a	n/a	79A
69/69B	11.638	n/a	n/a	79/79B	112 MHz
69C	11.679	n/a	n/a	79C


Intelsat 702's C-band EIRP


Intelsat 702's Ku-band EIRP


 Intelsat 703

General

Designation	23305 / 94064A
Launch date	6 Oct 1994
Country of origin	International
Mission	Telecommunications
Geostationary orbit	177°E
Launch vehicle	Atlas Centaur
Technical data

Specifications

C-band

Ku-band

EIRP coverage (dBW)

C-band

Ku-band

Has 4 Ku-band spot beams


Intelsat 703's C-band EIRP


Intelsat 703's Ku-band EIRP


 Intelsat 704

General

Designation	23461 / 95001A
Launch date	10 Jan 1995
Country of origin	International
Mission	Telecommunications
Geostationary orbit	66°E
Launch vehicle	Atlas Centaur

Began operations on 25 Feb 1995

Technical data

Specifications

C-band

Ku-band

EIRP coverage (dBW)

C-band

Ku-band

Could have better performances than the standard 7 series.


Intelsat 704's C-band EIRP


Intelsat 704's Ku-band EIRP


C-band of 704 & 705 ???

Main transponders	26
Backup transponders
Power
Bandwidth	10 transponders of 36 MHz 16 transponders of 72 MHz
Coverage and EIRP	Global beam: 34 dBW (36 MHz) Hemispheric beam: 40 dBW (2x36 MHz & 8x72 MHz) Zone beam: 40 dBW (2x36 MHz & 8x72 MHz) Spot beam: 41.6 dBW (36 MHz)
Polarization	circular R/L

Six 36 MHz transponders are either in global or in spot configuration.


 Intelsat 705

General

Designation	23528 / 95013A
Launch date	22 Mar 1995
Country of origin	International
Mission	Telecommunications
Geostationary orbit	50°W
Launch vehicle	Atlas Centaur

Test carried out in 56°W slot

Technical data

Specifications

C-band

Ku-band

EIRP coverage (dBW)

C-band

Ku-band

Could have better performances than the standard 7 series.


Intelsat 705's C-band EIRP


Intelsat 705's Ku-band EIRP


 Intelsat 706

General

Designation	23571 / 95023A
Launch date	17 May 1995
Country of origin	International
Mission	Telecommunications
Geostationary orbit	53°W
Launch vehicle	Ariane V73

Tests carried out in 56°W. Operational in mid-July 1995.

Technical data

Specifications

C-band

Ku-band

EIRP coverage (dBW)

C-band

Ku-band


Intelsat 706's C-band EIRP


Intelsat 706's Ku-band EIRP


 Intelsat 707

General

Designation	23816 / 96015A
Launch date	14 Mar 1996
Country of origin	International
Mission	Telecommunications
Geostationary orbit	1°W
Launch vehicle	Ariane V84

has 14 transponders in Ku-band

The insured value of the satellite, launch and insurance was $319.1 million.

Technical data

Specifications

C-band

Ku-band


 Intelsat 708

General

Designation	FTO
Launch date	14 Feb 1996
Country of origin	International
Mission	Telecommunications
Geostationary orbit	50°W
Launch vehicle	Long March 3B
Launch site	Xichang

The launch vehicle went off course shortly after leaving the pad and was destroyed about 20s after liftoff with its payload. Six people were killed and 57 injured, officially. Unofficial, deaths were said to be hundreds, and injured in the thousands. Two seconds after lift-off of the Long March 3B, the inertia platform became abnormal and the inertia baseline veered.

The satellite was insured for $205 million.

Technical data

Specifications

C-band

Ku-band


 Intelsat 709

General

Designation
Launch date	planned in Jul 1996
Country of origin	International
Mission	Telecommunications
Geostationary orbit	56°W
Launch vehicle	Ariane 44LP
Launch site
Technical data

Specifications

C-band

Ku-band


 Intelsat 801

General

Designation
Launch date	planned in Oct 1996
Country of origin	International
Mission	Telecommunications
Geostationary orbit	174°E
Launch vehicle	Ariane 44LP
Launch site
Technical data

Specifications

C-band

Ku-band


 Intelsat 802

General

Designation
Launch date	planned in Jan 1997
Country of origin	International
Mission	Telecommunications
Geostationary orbit	177°E
Launch vehicle	Ariane 44LP
Launch site
Technical data

Specifications

C-band

Ku-band


 Intelsat 803

General

Designation
Launch date	planned in Apr 1997
Country of origin	International
Mission	Telecommunications
Geostationary orbit	64°E
Launch vehicle	Ariane 44LP
Launch site
Technical data

Specifications

C-band

Ku-band


 Intelsat 804

General

Designation
Launch date	planned in Jul 1997
Country of origin	International
Mission	Telecommunications
Geostationary orbit	21.5°W
Launch vehicle	Ariane 44LP
Launch site
Technical data

Specifications

C-band

Ku-band


 Intelsat 805

Part of the 8A series

General

Designation
Launch date	planned in Aug 1997
Country of origin	International
Mission	Telecommunications
Geostationary orbit	110.5°E
Launch vehicle	Atlas 2AS
Launch site
Technical data

Specifications

C-band

Main transponders
Backup transponders
Power
Bandwidth
Coverage & EIRP	Zone or/and Hemi: 36 dBW no global nor spot beam
Polarization
Ku-band

Main transponders
Backup transponders
Power
Bandwidth
Coverage & EIRP	1 spot: 42 dBW
Polarization


 Intelsat 806

part of the 8A series

General

Designation
Launch date	planned in Dec 1997
Country of origin	International
Mission	Telecommunications
Geostationary orbit	40.5°W
Launch vehicle	Atlas 2AS
Launch site
Technical data

Specifications

C-band

Main transponders
Backup transponders
Power
Bandwidth
Coverage & EIRP	Zone or/and Hemi: 37.5 dBW no global nor spot beam
Polarization
Ku-band

Main transponders
Backup transponders
Power
Bandwidth
Coverage & EIRP	1 spot: 48 dBW
Polarization


Intelsat shift plans

707	1°W

702	177°E

703	57°E

709	18°W

515	21.3°W

512	40.5°W

801	174°E

701	180°E

511	91.5°E

501	junk?

802	177°E

703	91.5°E

803	64°E

602	62°E

505	junk?

804	21.5°W

512	40.5°W or 33°E

502	junk?

806	40.5°W

512	?

805	110.5°E


 Program: Intercosmos

Cooperation program created in 1967 between countries of the former East block. It was controlled by the Soviets and worked without money exchange, each state payed for the research in his own country and USSR launched the rockets (Intercosmos). The mission of the program was scientific research.

That program enabled cosmonauts of member states to fly.


Program: Intercosmos

Intercosmos 01

Intercosmos 18

Intercosmos Bulgaria 1300


 Intercosmos 01

General

Designation	04128 / 69088A
Launch date	14 Oct 1969
Country of origin	CIS
Mission	Scientific: high atmosphere study
Perigee/Apogee	264/617 km
Inclination	48.3°
Period	93.4 min
Launch vehicle
Launch site	Kapustin Yar
End of life

Decay	2 Jan 1970


 Intercosmos 18

General

Designation	11082 / 78099A
Launch date	24 Oct 1978
Country of origin	CIS
Mission	Scientific: ionosphere and magnetosphere study
Perigee/Apogee	403/757 km
Inclination	83°
Period	96.3 min
Launch vehicle
Launch site	Plesetsk
End of life

Decay	17 Mar 1981


 Intercosmos Bulgaria 1300

Also called Intercosmos 22

General

Designation	12645 / 81075A
Launch date	7 Aug 1981
Country of origin	Bulgaria
Mission	Scientific
Perigee/Apogee	788/882 km
Inclination	81.2°
Period	101.6 min
Launch vehicle
Launch site	Plesetsk
Mass at launch	350 kg


 Program: Intersputnik

Organization created in 1971 by the former USSR; started working in 1972. It was aimed to break Intelsat's monopoly (they didn't expect members not to belong to other telecommunications organizations). In 1987, 16 states belonged to the organization (Intercosmos members and other friend states).

Today Intersputnik has the following 22 members:
Afghanistan, Belarus, Bulgaria, Cuba, Czechoslovakia, Georgia, Germany, Hungary, Kazakhstan, Kirghistan, North-Korea, Laos, Mongolia, Nicaragua, Poland, Tajikistan, Turkmenistan, Romania, Russia, Syria, Yemen and Vietnam.

Intersputnik used Molniya satellites before turning to geostationary satellites (Raduga, Gorizont, Gals and Express). Earth stations use typical 12 m antennas.

Contact

Intersputnik

2 Smolensky Lane 1/4, Moscow, 121099, CIS

Tel: +7-95-244-0333

Fax: +7-95-253-9906

Email: dir@intersputnik.msk.ru

Contact

Informcosmos

16 Kazakova Street, Moscow 103064 Russia

Tel: +7-095-261-5494

Fax: +7-095-261-0090


Intersputnik 8
 Program: Intersputnik 8

Russian telecommunication satellite program lead by Intersputnik. A special purpose company was formed with Daimler Benz Aerospace (Germany) and Aerospatiale (France).

First satellite to be launched in late 1998 over the Indian Ocean. Another one will be positioned over the Atlantic Ocean in mid-1999.

Also for 1997, the Gals R12 project: 12 Ku-band transponders of 27 MHz, 7 years lifetime satellite

Technical data

Specifications

Prime contractor	Aerospatiale
Platform
Mass at launch
Mass in orbit
Dimension
Solar array
Stabilization
DC power
Design lifetime	> 15 years

SS/Loral will manufacture basic subsystems such as satellite repeaters and Daimler-Benz Aerospace will provide antennas, solar arrays and an attitude control system.

C-band

Main transponders	24
Backup transponders
Power
Bandwidth	36 MHz?
Coverage	global and regional
EIRP	37 - 40 dBW
Polarization
Ku-band

Main transponders	16
Backup transponders
Power
Bandwidth	54 and 72 MHz?
Coverage
EIRP	48 - 53 dBW
Polarization


 IRAS

Infra Red Astronomy Satellite

General

Designation	13777 / 83004A
Launch date	26 Jan 1983
Country of origin	Netherlands, United Kingdom and United States
Mission	Scientific: IR astronomy
Perigee/Apogee	884/903 km
Inclination	99°
Period	102.9 min
Launch vehicle	Thor Delta #166

It mapped 250,000 IR sources in the 300 days before its helium coolant was exhausted.

End of life

Out of service	23 Nov 1983
Technical data

Specifications

Industrial responsabilities	Netherlands Aerospace Agency (bus) NASA Ames Research Center, JPL (telescope) SERC (TT&C and data collection) Prime contractors: ICIRAS (bus) Ball Aerospace (telescope) Perkin-Elmer (optics)
Mass at launch	1077 kg
Telescope mass	810 kg
Diameter	2.2 m
Height	3.6 m
Solar array	5 m² (2 panels)
Stabilization	3 axis
DC power	EOL: 500 W
Design lifetime	11 months
Payload

Ritchey-Chretien-type reflecting telescope with a local plane array of 62 IR detectors surrounded by a dewar containing 475 l of liquid helium. Plus 2 photometers and a low-resolution spectrometer.

Telescope diameter	0.57 m
Focal length	5.5 m
Field of view	30 arcmin

Spectral range:

IR Telescope	(band 1) 8.5-15 µm (band 2) 19-30 µm (band 3) 40-80 µm (band 4) 83-119 µm
Spectrometer	7.4-23 µm
Short wavelength photometer	4.1-8 µm

Cooling system by evaporated helium

Temperature control	2 K
Telemetry/data	S-band (1 Mbps)


Iridium
 Program: Iridium

As the network was originaly though with 77 satellites, it was named after the 77th element in the periodical table

Mobile telecommuncation network operated by Motorola Satellite Communications Inc.

Network of 66 satellites (+ 7 spares) on a 785 km altitude orbit, 11 satellites on 6 polar orbits

Launches

12 satellites in 6 launches by Long March 2C from Taiyuan with unique "smart dispenser" (option for 4 more launches); July 1996

40 satellites in 8 launches by Delta 2

21 satellites in 3 launches by Proton

Overview

Orbit type	LEO
Orbit range	780 km
Nb of satellites	66 + 6 backup
Nb of planes	6
Inclination	86.4°
Nb beams per satellite	48
Coverage	4700 km2
Modulation	FNMA/TDMA
Mobile uplink freq.	L-Band: 1616 - 1626.5 MHz
Satellite mass	725 kg
Coverage	Worldwide
Operational date	1998 (planned)
Specifications

Prime contractor	Lockheed
Platform	Iridium
Mass at launch
Mass in orbit
Dimension	1 x 2 m
Solar array
Stabilization	3 axis
DC power
Design lifetime	5 years
Payload

Modulation	TDMA (Time Division Multiple Access)
Capacity	3840 phone circuits
Voice	4800 bps
Fax	2400
Data	2400 bps
Total Bandwith	200 MHz
Mobile links	1.5/1.6 GHz
Ground links	Ku-band
Intersatellite links	Ka-band: 18.8-20.2/27.5-30 GHz

On-board commutation


 Program: IRS

Indian Remote Sensing

Indian program to develop an indigenous capability to image Earth, particulary India. Mission: ground water exploration, land use, forest and flood mapping, inventory of surface water.


Program: IRS

IRS 1A

IRS 1B

IRS 1C

IRS 1D

IRS 1E

IRS 2A

IRS P2

IRS P3


IRS's specifications

Prime contractor	ISRO
Mass at launch	1150 kg
Dimension	1.6 x 1.56 x 1.1 m
Solar array	8.5 m²
Stabilization	3 axis
Design lifetime	3 years


IRS's payload

LISS 1 (Linear Imaging Self Scanner) with CCD detector arrays

Wavebands	0.45-0.52 µm (visible): sedimetation and coastal studies 0.52-0.59 µm (visible): vegetation. rock and soil discremination 0.62-0.68 µm (visible): chlorophyll absorption in vegetation. rock/soil 0.77-0.86 µm (IR): moisture in vegetation. land/water discremination
Resolution	72.5 m
Swath width	148 km
LISS 2 A & B (2 identical push-broom scanners with CCD detector arrays

Wavebands	as LISS 1
Resolution	36.25 m
Swath width	74 km either side of ground track with 3 km overlap: total 145 km

IRS 1C and D to feature near and shortwave IR sensors with 20 m resolution (color); 10 m (monochrome)


 IRS 1A

General

Designation	18960 / 88021A
Launch date	17 Mar 1988
Country of origin	India
Mission	Remote sensing
Perigee/Apogee	893/913 km
Inclination	98.8°
Period	103.1 min
Launch vehicle	Vostok
Launch site	Tyuratam
Mass at launch	960 kg

First commercial satellite launched by the CIS's organization Glavcosmos.

Technical data

Specifications

Payload


 IRS 1B

General

Designation	21688 / 91061A
Launch date	29 Aug 1991
Country of origin	India
Mission	Remote sensing
Perigee/Apogee	890/917 km
Inclination	99.1°
Period	103.1 min
Launch vehicle	Vostok
Launch site	Tyuratam
Technical data

Specifications

Payload


 IRS 1E

General

Launch date	20 Sep 1993
Country of origin	India
Mission	Remote sensing
Launch vehicle	PSLV #1
End of life

Out of service	20 Sep 1993
Cause	launcher failure, the payload ended in the ocean


 IRS P2

General

Designation	23323 / 94068A
Launch date	15 Oct 1994
Country of origin	India
Mission	Remote sensing
Perigee/Apogee	818/820 km
Inclination	98.7°
Period	102.3 min
Launch vehicle	PSLV #2

The spacecraft is in a Sun-synchronous orbit and carries a linear imaging self-scanner camera. The images will be marketed through a private company in the U.S.A.

Technical data

Specifications

Prime contractor	ISRO
Platform	IRS P
Mass at launch	870 kg
Mass in orbit
Length
Width
Height
Stabilization	3 axis
DC power
Design lifetime
LISS 2 A & B (2 identical push-broom scanners with CCD detector arrays

Wavebands	0.45-0.52 µm (visible): sedimetation and coastal studies 0.52-0.59 µm (visible): vegetation. rock and soil discremination 0.62-0.68 µm (visible): chlorophyll absorption in vegetation. rock/soil 0.77-0.86 µm (IR): moisture in vegetation. land/water discremination
Resolution	36.25 m
Swath width	74 km either side of ground track with 3 km overlap: total 145 km


 IRS 1C

General

Designation	23751 / 95072A
Launch date	28 Dec 1995 at 06:45 UT
Country of origin	India
Mission	Remote sensing
Perigee/Apogee	816/818 km (sun-synchronous)
Inclination	98.6°
Period	101 min
Launch vehicle	Molniya M
Launch site	Tyuratam

This was the first Russian launch into a retrograde (99 degree) orbit using the Molniya-M four stage rocket; earlier Russian retrograde launches used the Vostok rocket which has now been retired. The The Block-I third stage appears to have been suborbital, the first time such a flight profile has been used.

Launched by Glavkosmos, Russia's commercial space organisation. The launch contract between Russia and India cost 60 billion roubles ($12.9 million).

The American Esosat company has a contract to commercially distribute the data generated by this satellite so as the 9 other remote sensing satellites to be launched by ISRO during the 10-year period ending 2005. This contract is worth a billion dollar. Eosat has been receiving data from IRS 1B since June 1994 and from IRS-P2 since march this year on an experimental basis. Its ground station at Norman in Oklahoma was the first to receive IRS data outside India.

Technical data

Specifications

Payload

The IRS-1C is more advanced than earlier Indian remote sensing satellites, with a 6 m resolution panchromatic camera and a 20 m resolution multispectral camera.


 IRS P3

General

Designation	23827 / 96017A
Launch date	21 Mar 1996
Country of origin	India
Mission	Remote sensing
Perigee/Apogee	802/848 km
Inclination	98.8°
Period
Launch vehicle	PSLV #3
Mass at launch	930 kg

Includes an X-ray astronomy payload and a Widefield scanned + C-band antenna


 IRS 1D

to be launched in 1998 by a PSLV (should be PSLV-CI, 18 to 24 months after launch of IRS P3)


 IRS 2A

to be launched in 1999 by a PSLV


 IRT

General

Designation	14689 / 84011C
Launch date	5 Feb 1984
Country of origin	United States
Mission	Scientific
Perigee/Apogee	279/288 km
Inclination	28.5°
Period	90.2 min
Launch vehicle	STS 11

IRT was a inflatable balloon to be used as a rendezvous target to get practise for shuttle rendezvous manoeuvres. IRT blow appart shortly after beeing released.

End of life

Cause	Retrieved by the Shuttle
Decay	11 Feb 1984


 Program: ISEE

International Sun Earth Explorer

International scientific program

The 3rd satellite of the program, launched on 12 Aug 1978 was placed on a Sun orbit thus it isn't detailed in here. It has observed the Giacobini-Zinner comet on 11 Sep 1985.


Program: ISEE

ISEE 1

ISEE 2


 ISEE 1

General

Designation	10422 / 77102A
Launch date	22 Oct 1977
Country of origin	International
Mission	Scientific: magnetosphere study
Perigee/Apogee	436/137806 km
Inclination	12.7°
Period	3441 min
Launch vehicle	Thor Delta #135

Built by NASA

End of life

Decay	26 Sep 1987


 ISEE 2

General

Designation	10423 / 77102B
Launch date	22 Oct 1977
Country of origin	International
Mission	Scientific: magnetosphere study
Perigee/Apogee	406/137765 km
Inclination	13.5°
Period	3438.5 min
Launch vehicle	Thor Delta #135

Built by ESA

End of life

Decay	26 Sep 1987


 Program: Isis

Canadian scientific program for ionospheric studies


Program: Isis

Isis 1

Isis 2


 Isis 1

General

Designation	03669 / 69009A
Launch date	30 Jan 1969
Country of origin	Canada
Mission	Scientific: ionosphere study
Perigee/Apogee	574/3470 km
Inclination	88.4°
Period	127.7 min
Launch vehicle	Thor Delta #65
Mass at launch	237 kg


 Isis 2

General

Designation	05104 / 71024A
Launch date	1 Apr 1971
Country of origin	Canada
Mission	Scientific: ionosphere study
Perigee/Apogee	1353/1423 km
Inclination	88.5°
Period	113.5 min
Launch vehicle	Thor Delta #84
Mass at launch	262 kg


 ISO

Infrared Space Observatory

General

Designation	23715 / 95062A
Launch date	17 Nov 1995
Country of origin	Europe
Operator	ESTEC (European Space TEchnology Center) for ESA
Mission	Scientific: IR astronomy
Perigee/Apogee	1036/70578 km
Inclination	5.2°
Period	1436 min
Launch vehicle	Ariane V80

The satellite was initially planned for 1993 but the mission was delayed for two years while engineers worked on problems related to the temperature control system. The two-year delay added 20 percent to the project's final cost of $850 million for the satellite and launch. US astronomers will be granted 20 percent of the ISO's observation time in exchange for ground station support.

The first light image was taken on Nov 28.

The instruments were kept at a very low temperature (-270°C) in a cryostat wich contained 2400 liters of superfluid helium at liftoff.

Technical data

Specifications

Prime contractor	Aerospatiale
Platform
Mass at launch	2498 kg
Payload mass	1515 kg
Mass in orbit	2418 kg
Dimension	3.56 x 2.77 x 5.31 m
Solar array
Stabilization	3 axis
DC power
Design lifetime	1.5 years
Cassegrain telescope

Diameter	0.6 m
Focal length	9.0 m
Camera	ISOCAM
Temperature control	3K (-270°C)
Other payloads

Imaging photopolarimeter: ISOPHOT

Long Wavelength Spectrometer: LWS

Short Wavelength Spectrometer: SWS

Frequency bands

ISOCAM	3-17 µm
ISOPHOT	3-200 µm
LWS	45-180 µm
SWS	3-45 µm

Pointing stability: 2.7 arcsecs

Telemetry: 32 kbps (S-band: 2266.500 MHz)


 Program: Italsat

Italian experimental satellites operated by the Telespazio

Contact

Telespazio

Via Alberto Bergamini 50, Roma, 00159, Italia

Tel: +39-6-4987-2240

Fax: +39-6-4987-2743


Program: Italsat

Italsat 1

Italsat 2


 Italsat 1

General

Designation	21055 / 91003A
Launch date	15 Jan 1991
Country of origin	Italy
Mission	Telecommunications
Geostationary orbit	13.2°E
Launch vehicle	Ariane V41
Technical data

Specifications

Prime contractor	Selenia Spazio
Platform	Italsat
Mass at launch	1850 kg
Mass in orbit	1122 kg
Payload mass	273.4 kg: transponders: 198 kg, antennas: 75.4 kg)
Dimension	3.5 x 2.7 x 2.3 m
Solar array	21.8 m span
Stabilization	3 axis
DC power	EOL: equinox: 1760 W, solstice: 1633 W
Payload power	937 W
Design lifetime	6 years
Ka-band

Main transponders	3 in 20/30 GHz: national beam 6 in 20/60 GHz: multi-beam
Backup transponders	2 in 20/30 GHz 4 in 20/60 GHz
Power	20 W (TWTA)
Bandwidth	national beam: 36 MHz multi-beam: 120 MHz
Coverage	national beam: all Italy multi-beam: 6 spots
EIRP	national beam: 42.2 dBW multi-beam: 57 dBW
Polarization

Equipped with 1 (+1 backup) 1 W propagation beacon, EIRP 27 dBW


 Italsat 2

General

Designation
Launch date	planned in mid 1996
Country of origin	Italy
Mission	Telecommunications
Geostationary orbit	13.2°E
Launch vehicle	Ariane
Launch site
Technical data

Specifications

Prime contractor	Selenia Spazio
Platform	Italsat
Mass at launch	1983 kg
Mass in orbit	1185 kg
Payload mass	275 kg
Dimension	3.5 x 2.7 x 2.3 m
Solar array	24 m span
Stabilization	3 axis
DC power	EOL: solstice: 1990 W
Payload power	1266 W
Design lifetime	8 years
Beacons	Telemetry: 18.685 & 2.202 GHz Command: 2.028 GHz
Ka-band (20/30 GHz)

Main transponders	3 national beam + 6 multi-beam
Backup transponders
Power	20 W (TWTA)
Bandwidth	national beam: 36 MHz multi-beam: 110 MHz
Coverage	national beam: all Italy multi-beam: 6 spots
EIRP	national beam: 48 dBW multi-beam: 54 dBW
Polarization
European Mobile System (EMS) payload

Main transponders	L-band (1.5/1.6 GHz): 3 (forward) Ku-band (12/14 GHz): 12 (return)
Power	20 W
Bandwidth	L-band: 4 MHz Ku-band: 0.9 MHz
Coverage	Europe
EIRP	L-band: 42.5 dBW Ku-band: 32 dBW


 Itamsat

Also called IO-26 or Oscar 26

General

Designation	22826 / 93061D
Launch date	26 Sep 1993
Country of origin	Italy
Mission	Telecommunications
Perigee/Apogee	789/803 km
Inclination	98.7°
Period	100.8 min
Launch vehicle	Ariane V59
Technical data

Specifications

Prime contractor	Associazione Radioamatori Italiani
Platform	Amsat-NA Microsat
Mass at launch	12.5 kg
Mass in orbit
Length	230 mm
Width	230 mm
Height	235 mm
Stabilization	magnetic
DC power
Design lifetime	7-10 years
Frequency chart (MHz)

Downlink freq.	Transponder/Beacon	Mode
435.820		?
435.870		1200 bps PSK Digital
Uplink freq.	Transponder/Beacon	Mode
145.875		1200 bps FM Digital
145.900		1200 bps FM Digital
145.925		1200 bps FM Digital
145.950		1200 bps FM Digital


Itos
 Itos A

Improved Tiros Operational Satellite, also called Tiros M

General

Designation	04320 / 70008A
Launch date	23 Jan 1970
Country of origin	United States
Mission	Meteorology
Perigee/Apogee	1431/1477 km
Inclination	101.4°
Period	115 min
Launch vehicle	Thor Delta #76
Mass at launch	310 kg

This satellite is an evolved Tiros: it enables real time observation, night and day.


 IUE

International Ultraviolet Explorer

General

Designation	10637 / 78012A
Launch date	26 Jan 1978
Country of origin	International
Operator	NASA
Mission	Scientific: UV astronomy
Perigee/Apogee	30252/41315 km
Inclination	34.5°
Period	1435.9 min
Launch vehicle	Thor Delta #132
Mass at launch	671 kg

A joint NASA/ESA/SERC (Search and Engineering Research Council) observatory satellite designed for ultraviolet spectrometry of cosmic UV sources. ESA's contribution was the construction of the spacecraft's solar panels and a ground station at Villafranca, Spain.

On 1st October 1995 the primary control of the still operating spacecraft was transferred from NASA to ESA. This because of NASA's cost reduction efforts.

Contact

NASA

http://iuewww.gsfc.nasa.gov/iuedac/iuedac_homepage.html

Technical data

Specifications

Mass at launch	644 kg
Length	4.17 m
Width	1.45 m
Solar array	45 m²
Stabilization	3 axis
Design lifetime	3 years

Payload: 0.45 m diameter UV telescope

Transmits on 136.86 MHz


 Program: Jcsat

Japanese telecommunication program operated by Japan Communications Satellite Co (JSAT, Kabushiki-gaisha Nihon Sateraito Sisutemuzu). JSAT was formed in 1993 by the merger of Japan Communications Satellite Co (JCSAT, which operated the first two JCSAT satellites) and Satellite Japan Corp (SAJAC).

It is Japan's first commercial satellite system providing TV and cable distribution, telephony, business services and satellite news gathering.

Contact

Japan Satellite Systems Inc. (JSAT)

Toranomon 17 Mori Bldg. 5th Fl., 1-26-5 Toranomon, Minato-ku, Tokyo 105 Japan

Tel: +81-3-5511-7778

Fax: +81-3-3597-0601


Program: Jcsat

Jcsat 1

Jcsat 2

Jcsat 3

Jcsat 4


Jcsat 1 & 2's specifications

Prime contractor	Hughes
Platform	HS-393
Mass at launch	2280 kg
Mass in orbit	1376 kg
Diameter	3.66 m
Height	10 m deployed
Stabilization	Spin stabilized
DC power	BOL: 2240 W
Design lifetime	10 years


Jcsat 1 & 2's Ku-band

Main transponders	32
Backup transponders	8
Power	20 W (TWTA)
Bandwidth	27 MHz
Coverage	Japan and offshore territories
EIRP	51 dBW
Polarization


ASC's C-band transponder frequency chart
 Jcsat 1 & 2's transponder frequency chart (GHz)

Horizontal Uplink	Horizontal Downlink	Transponder	Vertical Downlink	Vertical Uplink
14.01625		1	12.26825
	12.28325	2		14.03125
14.04625		3	12.29825
	12.31325	4		14.06125
14.07625		5	12.32825
	12.34325	6		14.09125
14.10625		7	12.35825
	12.37325	8		14.12125
14.13625		9	12.38825
	12.40325	10		14.15125
14.16625		11	12.41825
	12.43325	12		14.18125
14.19625		13	12.44825
	12.46325	14		14.21125
14.22625		15	12.47825
	12.49325	16		14.24125
14.25625		17	12.50825
	12.52325	18		14.27125
14.28625		19	12.53825
	12.55325	20		14.30125
14.31625		21	12.56825
	12.58325	22		14.33125
14.34625		23	12.59825
	12.61325	24		14.36125
14.37625		25	12.62825
	12.64325	26		14.39125
14.40625		27	12.65825
	12.67325	28		14.42125
14.43625		29	12.68825
	12.70325	30		14.45125
14.46625		31	12.71825
	12.73325	32		14.48125


Jcsat 1 & 2's EIRP


 Jcsat 1

General

Designation	19874 / 89020A
Launch date	6 Mar 1989
Country of origin	Japan
Mission	Telecommunications
Geostationary orbit	150°E
Launch vehicle	Ariane V29

Due to a leak in the fuel tank, the satellite will reach end of life in mid-1997

Technical data

Specifications

Ku-band

Transponder frequency chart

EIRP coverage (dBW)


 Jcsat 2

General

Designation	20402 / 90001B
Launch date	1 Jan 1990
Country of origin	Japan
Mission	Telecommunications
Geostationary orbit	154°E
Launch vehicle	Titan 3
Launch site	Cape Canaveral
Technical data

Specifications

Ku-band

Transponder frequency chart

EIRP coverage (dBW)


 Jcsat 3

General

Designation	23649 / 95043A
Launch date	29 Aug 1995
Country of origin	Japan
Mission	Telecommunications
Geostationary orbit	128°E
Launch vehicle	Atlas Centaur #94

GTO: 167 km x 81432 km x 23.5°

In December 1995 it was made public that the satellite had a "minor defect" which caused the next satellite Jcsat 4 to be ordered ASAP

In 1995 leases were said to cost ¥550 million a year for 27 MHz transponders and ¥600 million a year for 36 MHz transponders.

Technical data

EIRP coverage (dBW)

C-band

Ku-band

Specifications

Prime contractor	Hughes
Platform	HS-601
Mass at launch
Mass in orbit
Length
Width
Height
Stabilization	3 axis
DC power	4600 W
Design lifetime	12 years

NEC Corp. of Japan is a major subcontractor to Hughes for the payload electronics.

C-band

Main transponders	12
Backup transponders
Power	34 W (SSPA)
Bandwidth	36 MHz
Coverage	Asia & Australia
EIRP	37 dBW
Polarization	linear
Ku-band

Main transponders	28
Backup transponders
Power	60 W (TWTA)
Bandwidth	16 transponders of 27 MHz 12 transponders of 36 MHz
Coverage & EIRP	Japan: 55 dBW Eastern Asia, India & Australia: 43-35 dBW
Polarization	Linear


Jcsat 3's C-band EIRP


Jcsat 3's Ku-band EIRP


 Jcsat 4

General

Designation
Launch date	planned in Jan 1997
Country of origin	Japan
Mission	Telecommunications
Geostationary orbit	124°E
Launch vehicle	Atlas 2AS
Launch site	Cape Canaveral LC36A

Satellite ordered after a Jcsat 3 problem was detected

Technical data

Specifications

Prime contractor	Hughes
Platform	HS-601 (#58)
Mass at launch
Mass in orbit
Length
Width
Height
Stabilization	3 axis
DC power	5000 W
Design lifetime	12 years

Features 4 octagonal communications antennas

C-band

Main transponders	12
Backup transponders
Power	34 W (SSPA)
Bandwidth	36 MHz
Coverage	Asia & Australia
EIRP	37 dBW
Polarization	linear
Ku-band

Main transponders	24
Backup transponders
Power	60 W (TWTA) + four 90 W (TWTA) for 4 36 MHz transponders
Bandwidth	8 transponders of 36 MHz 16 transponders of 27 MHz (4 transponders can be switched to 54 MHz with 120 W)
Coverage & EIRP	Japan: 55 dBW Eastern Asia, India & Australia: 43-35 dBW
Polarization	Linear


 JERS 1

Japanese Earth Resource Sensing satellite, also called Fuyo 1

General

Designation	21867 / 92007A
Launch date	11 Feb 1992 at 01:50 UT
Country of origin	Japan
Mission	Remote sensing
Perigee/Apogee	567/568 km
Inclination	97.7°
Period	96 min
Launch vehicle	H1
Launch site	Tanegashima
Mass at launch	1340 kg

Had problems to open out its SAR antenna that were solved. Is working with 1 third of its power (4000 W instead of 12) thus the performance is not maximum

Technical data

Specifications

Prime contractor	Mitsubishi
Mass at launch	1400 kg
Length	0.93 m
Width	1.83 m
Height	3.16 m
Solar array	7 x 3.5 m
SAR Antenna	11.9 x 2.4 m
Stabilization	3 axis
Design lifetime	2 years
SAR (Synthetic Aperture Radar)

Frequency	1.3 GHz (L-band)
Resolution	18 x 18 m
Swath width	75 km

Mission: high resolution monitoring of land use and type, glacier extent, snow cover, surface topography, ocean currents and waves.

OPS (Optical Scanner)

Wavebands	0.52-0.6 µm (visible) 0.63-0.69 µm (visible) 0.76-0.96 µm (near IR) 1.6-1.7 µm (near IR) 2.0-2.4 µm (near IR)
Resolution	18 x 24 m
Swath width	75 km

Mission: pollution monitoring in oceans and lakes, land use classification, cloud and snow discrimination.


 Program: KH

Key Hole

American military reconnaissance program. The first satellites had a very limited lifetime.

from 1959 to 1992: 266 launched including 50 failures

Samos KH 1 series

Satellite And Missile Observatory System

KH 1 series

8 satellites launched

Discovery: kh 1, 2 & 3

1st generation: discovery, samos and KH 3

KH 4 series

Corona

8 satellites launched

KH 4A series

Corona adv

41 satellites launched

1.5 t, launched by Thor Agena, resolution = 3 m, capsule for retrieval of data

KH 4B series

Corona adv (1966-72)

1.9 t, launched by Thor Agena, resolution = 1.5 m, capsule for retrieval of data?

KH 5 series

Argon

launched by Thor Agena, topographical camera, radio transmission

KH 6 series

Lanyard, samos adv

launched by Atlas Agena, program stopped in 1963

KH 7 series

Gambit

36 satellites launched

2 tons, launched by Atlas Agena, 50 cm resolution, 1963-67, capsule retrieval, high resolution camera

KH 8 series

Gambit adv

49 satellites launched

1966-85, 3.4 tons, titan 3b, high resolution camera + topographical camera + multispectral camera

KH 9 series

Hexagon or Big Bird

19 satellites launched

11.3 tons, titan 3d, 1971-86, replace KH 4B and KH 8

The images were returned on film contained in capsules. The typical orbit was a 250 km sun-synchronous orbit which was maintained against drag by frequent maneuvring engine firings. Lifetime was close to 18 months

KH 11 series

Kennan

At least 7 satellites launched

They operate on a sun-synchronous orbit (250/500 km for the first satellites, from KH 11-6 on 300/1000 km). Images are transmitted in real time via TDRS. Lifetime at least 4 years

13 tons, CCDs, 1976-88, 15 cm resolution

The constellation consists of two satellites in separate planes, spaced by the angle through which the Earth rotates during two of their orbital periods, about 48.7 deg. Each satellite repeats its groundtrack every four days; and the east satellite follows the west satellite's groundtrack two days later.

KH 12 series

Kennan adv


Program: KH

KH 1-2

KH 1-5

KH 4-01

KH 4A-03

KH 7-01

KH 9-01

KH 11-1

KH 11-2

KH 11-3

KH 11-6

KH 12-1

KH 12-2

KH 12-3


 KH 1-2

Also called Samos 2

General

Designation	00070 / 61001A
Launch date	31 Jan 1961
Country of origin	United States
Mission	Military: reconnaissance
Perigee/Apogee	474/557 km
Inclination	97.4°
Period	95 min
Launch vehicle	Atlas Agena B
Launch site	Vandenberg

First american spy satellite transmitting images by radio

End of life

Decay	21 Oct 1973


 KH 1-5

Also called Samos 5

General

Designation	00219 / 61035C
Launch date	22 Dec 1961
Country of origin	United States
Mission	Military: reconnaissance
Perigee/Apogee	187/310 km
Inclination	89.6°
Period	89.4 min
Launch vehicle
Launch site	Vandenberg
End of life

Decay	9 Jan 1962


 KH 4-01

Also called Close Look

General

Designation	00256 / 62007A
Launch date	7 Mar 1962
Country of origin	United States
Mission	Military: reconnaissance
Perigee/Apogee	236/686 km
Inclination	90.9°
Period	93.9 min
Launch vehicle
Launch site	Vandenberg
End of life

Decay	7 Jan 1963


 KH 4A-03

General

Designation	00578 / 63016A
Launch date	18 May 1963
Country of origin	United States
Mission	Military: reconnaissance
Perigee/Apogee	147/506 km
Inclination	91°
Period	74.5 min
Launch vehicle
Launch site	Vandenberg
End of life

Decay	27 May 1963


 KH 7-01

General

Designation	00618 / 63028A
Launch date	12 Jul 1963
Country of origin	United States
Mission	Military: reconnaissance
Perigee/Apogee	173/212 km
Inclination	95.3°
Period	88.3 min
Launch vehicle	Atlas Agena D
Launch site	Vandenberg
End of life

Decay	17 Jul 1963


 KH 9-01

General

Designation	05297 / 71056A
Launch date	15 Jun 1971
Country of origin	United States
Mission	Military: reconnaissance
Perigee/Apogee	180/300 km
Inclination	96.4°
Period	89.3 min
Launch vehicle
Launch site	Vandenberg
End of life

Decay	6 Aug 1971


 KH 11-1

General

Designation	09627 / 76125A
Launch date	19 Dec 1976
Country of origin	United States
Mission	Military: reconnaissance
Perigee/Apogee	246/531 km
Inclination	96.9°
Period	92.3 min
Launch vehicle
Launch site	Vandenberg
End of life

Decay	28 Jan 1979


 KH 11-2

General

Designation	10947 / 78060A
Launch date	14 Jun 1978
Country of origin	United States
Mission	Military: reconnaissance
Perigee/Apogee	223/509 km
Inclination	97°
Period	91.9 min
Launch vehicle
Launch site	Vandenberg
End of life

Decay	23 Aug 1981


 KH 11-3

General

Designation	11687 / 80010A
Launch date	7 Feb 1980
Country of origin	United States
Mission	Military: reconnaissance
Perigee/Apogee	220/498 km
Inclination	97°
Period	91.7 min
Launch vehicle
Launch site	Vandenberg
End of life

Decay	30 Oct 1982


 KH 11-6

Also called USA 006

General

Designation	15423 / 84122A
Launch date	4 Dec 1984
Country of origin	United States
Mission	Military: reconnaissance
Perigee/Apogee	n/a
Inclination	n/a
Period	n/a
Launch vehicle
Launch site	Vandenberg
End of life

Decay	Oct 1994?


 KH 12-1

Also called USA 053

General

Designation	20516 / 90019B
Launch date	28 Feb 1990
Country of origin	United States
Mission	Military: reconnaissance (Kennan advanced)
Perigee/Apogee	800 km
Inclination	65°
Period
Launch vehicle	STS 36
Mass at launch	14000 kg

Optical reconnaissance satellite. Believed resolution: 15 cm. Downlinks via TDRS. Built by Lockheed


 KH 12-2

Also called USA 086

General

Designation	22251 / 92083A
Launch date	28 Nov 1992
Country of origin	United States
Mission	Military: reconnaissance (Kennan advanced)
Perigee/Apogee	800 km
Inclination	97°
Period
Launch vehicle	Titan 4
Mass at launch	14000 kg

Optical reconnaissance satellite. Believed resolution: 15 cm. Downlinks via TDRS. Built by Lockheed

Was found in the orbit once occupied by KH 11-7


 KH 12-3

Also called USA 116

General

Designation	23728 / 95066A
Launch date	5 Dec 1995 at 21:18 UT
Country of origin	United States
Mission	Military: reconnaissance (Kennan advanced or Crystal)
Perigee/Apogee	250/1000 km
Inclination	98.7°
Period
Launch vehicle	Titan 4
Mass at launch	14000 kg

Optical (and IR?) reconnaissance satellite. Believed resolution: 15 cm. Downlinks via TDRS. Built by Lockheed


 Program: Kitsat

Also named Uribyol

Korean program operated by the Korean Institute of Science and Technology


Program: Kitsat

Kitsat A

Kitsat B


 Kitsat A

Also called KO-23 or Oscar 23

General

Designation	22077 / 92052B
Launch date	10 Aug 1992
Country of origin	South Korea
Mission	Telecommunications
Perigee/Apogee	1304/1324 km
Inclination	66.1°
Period	111.9 min
Launch vehicle	Ariane V52
Mass at launch	50.5 kg

Function: Packet Radio Mailbox, Digipeater, a CCD camera experiment and a synthesized voice experiment. The Earth Imaging System (EIS) has 2 CCD cameras.

Technical data

Specifications

Prime contractor	Korean Advanced Institute of Science and Technology
Platform	SSTL (Surrey Satellite Technology Ltd.)
Mass at launch	50.5 kg
Mass in orbit
Length
Width
Height
Stabilization	3 axis (gravity gradient & magnetotorquer)
DC power
Design lifetime
Frequency chart

Uplink	9600 bps K9NG/G3RUH modulated FSK (FM) AX.25 145.850 145.900 MHz
Downlink	9600 bps K9NG/G3RUH modulated FSK (FM) AX.25 435.175 MHz


 Kitsat B

Also called KO-25 or Oscar 25

General

Designation	22830 / 93061H
Launch date	26 Sep 1993
Country of origin	South Korea
Mission	Telecommunications
Perigee/Apogee	787/803 km
Inclination	98.6°
Period	100.8 min
Launch vehicle	Ariane V59
Mass at launch	47.5 kg

It carries CCD cameras, store/forward communication equipment (HAM radio) and a radiation detector.

Technical data

Specifications

Prime contractor	SaTRec (Satellite Technology Research Center)
Platform	SSTL (Surrey Satellite Technology Ltd.)
Mass at launch	50.5 kg
Mass in orbit
Length	352 mm
Width	356 mm
Height	670 mm
Stabilization	3 axis (gravity gradient & magnetotorquer)
DC power
Design lifetime	5 years
Frequency chart (MHz)

Downlink freq.	Transponder/Beacon	Mode
435.175	T	9600 bps FSK FM Digital
436.500	T	9600 bps FSK FM Digital
Uplink freq.	Transponder/Beacon	Mode
145.870	T	9600 bps FSK FM Digital
145.980	T	9600 bps FSK FM Digital


 Program: Koreasat

Also called Mugunghwa (name of the national flower)

First Korean geostationary telecommunication program. The second generation satellites are planned for 2005

Contact

Koreasat - ETRI

PO Box 8, Daeduk Science Town Daejeon, 305-608, Korea

Tel: +82-42-880-6830

Fax: +82-42-860-6430


Program: Koreasat

Koreasat 1

Koreasat 2


Koreasat's specifications

Prime contractor	Lockheed Martin Astro Space
Platform	GE 3000
Mass at launch	1464 kg
Dry mass	652 kg
Payload mass	202 kg
Dimension	1.74 x 1.96 x 1.9 m
Stabilization	3 axis
DC power	BOL: 1600 W
Design lifetime	12 years

Beacons would be at: 12.25125, 12.25175 & 12.74875 GHz


Koreasat's Ku-band for telecom

Main transponders	12
Backup transponders
Power	12 W
Bandwidth	36 MHz
Coverage	South Korea
EIRP	52.5 dBW
G/T	16 dB/K
Polarization	linear
Frequencies	Uplink: 14.00-14.5 GHz Downlink: 12.25-12.75 GHZ


Koreasat's Ku-band for DBS

Main transponders	3
Backup transponders
Power	120 W
Bandwidth	27 MHz
Coverage	South Korea
EIRP	61 dBW
G/T	15 dB/K
Polarization	LHCP
Frequencies	Uplink: 14.5-14.8 GHz Downlink: 11.7-12.0 GHZ


Koreasat's telecom EIRP


Koreasat's DBS EIRP


 Koreasat 1

Also called Mugunghwa ho

General

Designation	23639 / 95041A
Launch date	5 Aug 1995 at 11:10 UT
Country of origin	South Korea
Mission	Telecommunications
Geostationary orbit	116°E
Launch vehicle	Delta 2 #228

The launch experienced a partial failure: a booster rocket to separate. The preliminary reports indicate that explosive lines on the Delta 2 vehicle were damaged by exposure to excessive temperatures, causing one of the solid motors not to separate. The booster separation malfunction was blamed on the heat-related failure of insulation protecting the rocket's booster separation circuits.

This resulted in a wrong orbit delivery. The satellite reached GEO at the end of August on its own and used part of is propellant. Thus its lifetime was reduced to 4.5 years.

Technical data

Specifications

Ku-band (telecom)

Ku-band (DBS)

EIRP coverage (dBW)

Telecom

DBS

Equipped with a Star 30 solid apogee motor. Carries 625 kg of fuel for the apogee motor and 187 kg of hydrazine propellant.


 Koreasat 2

Also called Mugunghwa 2

General

Designation	23768 / 96003A
Launch date	14 Jan 1996
Country of origin	South Korea
Mission	Telecommunications
Geostationary orbit	116°E
Launch vehicle	Delta 2 #231
Mass at launch	1608 kg
Technical data

Specifications

Ku-band (telecom)

Ku-band (DBS)

EIRP coverage (dBW)

Telecom

DBS


 Koronas 1

General

Designation	23019 / 94014A
Launch date	2 Mar 1994 at 03:24 UT
Country of origin	Russia-Ukrain
Mission	Scientific: ionosphere, magnetosphere and Sun study
Operator	RKA space agency (probably by the IKI science institute)
Perigee/Apogee	483/526 km
Inclination	82.5°
Period	94.7 min
Launch vehicle	Cyclone 3 (11K68)
Launch site	Plesetsk LC32

The payload was developed by the IZMIRAN institute (Institute of Terrestrial Magnetism in Moscow) and includes the Terek spectroheliometer, the RES-K solar x-ray spectrograph, the Helikon solar gamma ray detector, the SUVR-SP-C ultraviolet radiometer, the DIFOS optical photometer, and other instruments.

Built by NPO Yuzhnoe, platform: AUOS-SM


 L Star 1

General

Designation
Launch date	planned in early 1998
Country of origin	Thailand
Mission	Telecommunications
Geostationary orbit	116°E
Launch vehicle	Ariane
Launch site

Program of Asia Broadcasting and Communications Network Public Company, Limited (ABCN) of Bangkok. ABCN is a subsidiary of Thailand's M. Group. After launch, the satellite is to be handed over to Lao-Star Co. Ltd., a company held 80 percent by ABCN and 20 percent by the government of Laos. ABCN also awarded a contract to Telesat Canada to monitor and test the L-Star program as technical advisers.

The contract (2 satellites with launch) is worth $480 million

Technical data

Specifications

Prime contractor	Space Systems/Loral
Platform
Mass at launch	3500 kg
Mass in orbit
Dimension
Solar array
Stabilization
DC power	3600 W
Design lifetime	14 years
Ku-band

Main transponders	16 or 32?
Backup transponders
Power
Bandwidth
Coverage	wide coverage zone in Southeast Asia
EIRP
Polarization


 L Star 2

General

Designation
Launch date	planned in mid 1998
Country of origin	Thailand
Mission	Telecommunications
Geostationary orbit	?
Launch vehicle	Ariane
Launch site

See L Star 1 for more details... the satellites could be identical


 Program: Lacrosse

Also called Indigo

American military reconnaissance program

Equipped with a Synthetic Aperture Radar which provides 1 m resolution data. Lifetime = 5 years, 14 tons, built by Martin Marietta


Program: Lacrosse

Lacrosse 1

Lacrosse 2


 Lacrosse 1

Also called USA 034

General

Designation	19671 / 88106B
Launch date	2 Dec 1988
Country of origin	United States
Mission	Military: reconnaissance
Perigee/Apogee	700 km
Inclination	57°
Period
Launch vehicle	STS 27R


 Lacrosse 2

Also called USA 069

General

Designation	21147 / 91017A
Launch date	8 Mar 1991
Country of origin	United States
Mission	Military: reconnaissance
Perigee/Apogee	700 km
Inclination	68°
Period
Launch vehicle	Titan 4


 Program: Lageos

LAser GEOdynamic Satellite

American scientific program operated by CNR/PSN/NASA

Series of satellites designed to provide an orbiting benchmark for geodynamical studies of the Earth. Mission: accurate measurement of satellite's position with respect to Earth; determination of the planet's shape (geoid) and determination of tectonic plate movements associated with continental drift.


Program: Lageos

Lageos 1

Lageos 2


Lageos's specifications

Mass at launch	410 kg
Diameter	0.6 m
Stabilization	passive
Design lifetime	50 years


Lageos's payload

Retroreflectors mounted on the surface of the sphere

Number of retroreflectors	426 (422 fused silica, 4 germanium)
Individual diameter	3.8 cm
Accuracy	ground transmitter position can be determined to 10 cm; drift to 2 cm/year
Contruction material	aluminum with a brass core


 Lageos 1

General

Designation	08820 / 76039A
Launch date	4 May 1976
Country of origin	United States
Mission	Scientific: geodesy
Perigee/Apogee	5836/5947 km
Inclination	109.8°
Period	225.4 min
Launch vehicle	Thor Delta #123
Technical data

Specifications

Payload


 Lageos 2

General

Designation	22195 / 92070B
Launch date	22 Oct 1992
Country of origin	United States
Mission	Scientific: geodesy
Perigee/Apogee	5615/5952 km
Inclination	52.6°
Period	222.5 min
Launch vehicle	STS 52
Technical data

Specifications

Payload

Prime contractor: Aeritalia


 Program: Landsat

Also called ERTS (Earth Resources Technology Satellites)

The idea of a civil Earth observation program came in 1962 but the first Landsat was launched only 10 years after because of political and technical choices. In fact alot of technology was classified and could be used for civil purposes. Agencies like the Geological Survey had to put pressure to make the program start. The sensibility of the resolution was longly discussed (efficient but not too efficient!).

In 1984 the Congress gave EOSAT (Earth Observation SATellite corporation) the right to commercialize the pictures but it didn't make Landsat self financed.

Landsat 1 series

Made of Landsat 1, 2 & 3. Descending node at 09:30 and 18 days orbital cycle

Based on the Nimbus platform. Were equipped with the RBV (Return Beam Vidicon) TV camera and the MSS (MultiSpectral Scanner) radiometer. Such a camera had been used by the lunar observation program Ranger. The satellites transmit their data in real time to Eath stations when they are available otherwise the data is recorded on-board.

Has the same MSS as Landsat 4 & 5

Landsat 2 series

Made of Landsat 4 & 5. Descending node at 09:37 and 16 days orbital cycle

The data is transmitted by the TDRS network.

Specifications

Payload

Landsat 3 series

Made of Landsat 6 & 7. 16 days orbital cycle

Specifications

Payload


Program: Landsat

Landsat 1

Landsat 2

Landsat 3

Landsat 4

Landsat 5

Landsat 6

Landsat 7


Landsat 4 & 5's specifications

Prime contractor	GE Astro
Platform	MultiMission Spacecraft (MMS)
Mass at launch	1941 kg
Length	4 m
Stabilization	3 axis
Design lifetime	3 years


Landsat 4 & 5's payload

MMS (Multispectral Scanner System)

Wavebands	0.5-0.6 µm (green): mapping coastal features in sediment-laden water 0.6-0.7 µm (red): mapping roads and urban areas 0.7-0.8 µm (red to near IR): as below 0.8-1.1 µm (near IR): vegetation studies and mapping land/water boundaries
Resolution	80 m
Swath width	185 km
TM (Thematic Mapper)

Wavebands	0.45-0.52 µm (visible): soil/vegetation differentiation & coastal water mapping 0.52-0.60 µm (visible): vegetation mapping 0.63-0.69 µm (visible): plant species differentiation 0.76-0.90 µm (near IR): biomass survey 1.55-1.75 µm (IR): snow/cloud differentiation 10.4-12.5 µm (thermal IR): thermal mapping 2.08-1.35 µm (IR): geological mapping
Resolution	30 m (visible, near & middle IR); 120 m (thermal IR)
Swath width	185 km


Landsat 6 & 7's specifications

Prime contractor	GE Astro
Platform	Tiros N/DMSP
Mass at launch	2750 kg
Mass in orbit	2000 kg
Length	6.4 m
Width	1.22 m
Stabilization	3 axis
Design lifetime	5 years


Landsat 6 & 7's payload

MSS identical to Landsat 4 & 5

ETM (Enhanced Thematic Mapper)

Wavebands	0.45-0.52 µm (visible) 0.52-0.60 µm (visible) 0.63-0.69 µm (visible) 0.76-0.90 µm (near IR) 1.55-1.75 µm (IR) 10.4-12.5 µm (thermal IR) 2.08-2.35 µm (IR) 0.5-0.9 µm (panchromatic)
Resolution	15 m (panchromatic), 30 m (visible. near & middle IR)
Swath width	185 km
SeaWiFS (Sea-viewing Wide Field Sensor)

Wavebands	0.43-0.45 µm (visible): low chlorophyll 0.49-0.51 µm (visible): other pigments 0.55-0.57 µm (visible): baseline chlorophyll 0.65-0.67 µm (visible): subsurface scattering 0.74-1.78 µm (near IR): atmospheric correction 0.84-0.89 µm (near IR): atmospheric correction 10.5-11.5 µm (IR): sea-surface temperature 11.5-12.5 µm (IR): sea-surface temperature
Resolution	1.13 km (local area coverage) 4.5 km (global area coverage)
Swath width	2800 km
Revisit interval	1 day


 Landsat 1

Also called ERTS 1

General

Designation	06126 / 72058A
Launch date	23 Jul 1972
Country of origin	United States
Mission	Remote sensing
Perigee/Apogee	895/908 km
Inclination	99.4°
Period	103 min
Launch vehicle	Thor Delta #89
Mass at launch	816 kg

Has provided over 1 million multispectral photos

End of life

Out of service	1980


 Landsat 2

Also called ERTS 2

General

Designation	07615 / 75004A
Launch date	22 Jan 1975
Country of origin	United States
Mission	Remote sensing
Perigee/Apogee	898/912 km
Inclination	98.9°
Period	103.1 min
Launch vehicle	Thor Delta #107
End of life

Out of service	Feb 1982


 Landsat 3

Also called ERTS 3

General

Designation	10702 / 78026A
Launch date	5 Mar 1978
Country of origin	United States
Mission	Remote sensing
Perigee/Apogee	895/915 km
Inclination	98.9°
Period	103.1 min
Launch vehicle	Thor Delta #139


 Landsat 4

General

Designation	13367 / 82072A
Launch date	16 Jul 1982
Country of origin	United States
Mission	Remote sensing
Perigee/Apogee	696/708 km
Inclination	98.1°
Period	98.8 min
Launch vehicle	Thor Delta #163
Technical data

Specifications

Payload

Downlink frequency: 2229.5 / 2265.5 MHz


 Landsat 5

General

Designation	14780 / 84021A
Launch date	1 Mar 1984
Country of origin	United States
Mission	Remote sensing
Perigee/Apogee	698/706 km
Inclination	98.1°
Period	98.8 min
Launch vehicle	Thor Delta #174
Technical data

Specifications

Payload


 Landsat 6

General

Launch date	5 Oct 1993 at 17:56 UT
Country of origin	United States
Mission	Remote sensing
Launch vehicle	Titan 2G
Launch site	Vandenberg SLC4W
End of life

Out of service	5 Oct 1993
Cause	Attitude control failure

Cost: $220 million

After rupture of a hydrazine manifold disabled attitude control the satellite began to tumble at the start of the apogee-motor (Thiokol Star 37XFP) firing, and did not reach orbit.

Technical data

Specifications

Payload


 Landsat 7

General

Designation
Launch date	planned in May 1998
Country of origin	United States
Mission	Remote sensing
Perigee/Apogee	sun synchronous
Inclination
Period
Launch vehicle	Delta 2
Launch site	Vandenberg

Launch under the MELVS contract


 Program: LCS

American radar calibration military program


Program: LCS

LCS 1

LCS 2:see OV 2-1?

LCS 4


 LCS 1

General

Designation	01361 / 65034C
Launch date	6 May 1965
Country of origin	United States
Mission	Military
Perigee/Apogee	2786/2795 km
Inclination	32.1°
Period	145.6 min
Launch vehicle
Launch site	Cape Canaveral


 LCS 4

General

Designation	05396 / 71067F
Launch date	7 Aug 1971
Country of origin	United States
Mission	Military
Perigee/Apogee	779/910 km
Inclination	87.6°
Period	101.8 min
Launch vehicle
Launch site	Vandenberg
End of life

Decay	11 Jun 1972


 LDEF

Long Duration Exposure Facility

General

Designation	14898 / 84034B
Launch date	6 Apr 1984
Country of origin	United States
Mission	Scientific: Meteorite observation
Perigee/Apogee	344/348 km
Inclination	28.5°
Period	91.5 min
Launch vehicle	STS 13

Mass at retrieval: 10.5 t with 10000 samples

Developed by NASA (Langley Research Center)

End of life

Out of service	9 Jan 1990
Cause	Retrieved by STS 32R
Decay	20 Jan 1990


 Program: Leasat

LEAsed SATellite

American military telecommunication satellite program. The satellites (Syncom 4 series) are owned by HCI and leased to US Navy. They are believed to downlink in UHF- and X-band.


Program: Leasat

Leasat 1

Leasat 2

Leasat 3

Leasat 4

Leasat 5


Leasat's specifications

Prime contractor	Hughes
Platform	HS-381
Mass at launch
Mass in orbit
Dimension
Solar array
Stabilization
DC power
Design lifetime


Leasat's UHF-band

Main transponders	13
Backup transponders
Power
Bandwidth
Coverage
EIRP
Polarization


 Leasat 1

Also called Syncom 401

General

Designation	15384 / 84113C
Launch date	10 Nov 1984
Country of origin	United States
Mission	Military: telecommunications
Geostationary orbit
Launch vehicle	STS 19
End of life

Out of service	yes
Technical data

Specifications

UHF-band


 Leasat 2

Also called Syncom 402

General

Designation	15236 / 84093C
Launch date	30 Aug 1984
Country of origin	United States
Mission	Military: telecommunications
Geostationary orbit	see below
Launch vehicle	STS 23
Location

Begin	End	Position
L: 30 Aug 1984
early 1994	early 1994	73°E
Feb 1995		177.5°W, inclined
Technical data

Specifications

UHF-band


 Leasat 3

Also called Syncom 403

General

Designation	15643 / 85028C
Launch date	12 Apr 1985
Country of origin	United States
Mission	Military: telecommunications
Geostationary orbit	see below
Launch vehicle	STS 16

When released from STS 16 it failed to reach GEO and was repaired by STS 27

Location

Begin	End	Position
L: 12 Apr 1985
early 1994		105°W, inclined
Technical data

Specifications

UHF-band


 Leasat 4

Also called Syncom 404

General

Designation	15995 / 85076D
Launch date	29 Aug 1985
Country of origin	United States
Mission	Military: telecommunications
Geostationary orbit	n/a
Launch vehicle	STS 27
End of life

Out of service	Sep 1985
Cause	failed in GEO
Technical data

Specifications

UHF-band


 Leasat 5

Also called Syncom 405

General

Designation	20410 / 90002B
Launch date	9 Jan 1990
Country of origin	United States
Mission	Military: telecommunications
Geostationary orbit	see below
Launch vehicle	STS 32R
Location

Begin	End	Position
L: 12 Apr 1985
early 1994	early 1994	177°W
Feb 1995		71.5°W, inclined
Technical data

Specifications

UHF-band


 Program: LES

Lincoln Experimental Satellite

American military tactical program designed by the Lincoln lab


Program: LES

LES 1

LES 2

LES 3

LES 4

LES 5

LES 6

LES 8

LES 9


 LES 1

General

Designation	01002 / 65008C
Launch date	11 Feb 1965
Country of origin	United States
Mission	Military: ?
Perigee/Apogee	2783/2809 km
Inclination	32.1°
Period	145.8 min
Launch vehicle
Launch site	Cape Canaveral


 LES 2

General

Designation	01360 / 65034B
Launch date	6 May 1965
Country of origin	United States
Mission	Military: ?
Perigee/Apogee	2771/14810 km
Inclination	32.2°
Period	309.9 min
Launch vehicle
Launch site	Cape Canaveral


 LES 3

General

Designation	01941 / 65108D
Launch date	21 Dec 1965
Country of origin	United States
Mission	Military: ?
Perigee/Apogee	267/4829 km
Inclination	26.5°
Period	139.9 min
Launch vehicle
Launch site	Cape Canaveral
End of life

Decay	6 Apr 1968


 LES 4

General

Designation	01870 / 65108B
Launch date	21 Dec 1965
Country of origin	United States
Mission	Military: ?
Perigee/Apogee	189/33632 km
Inclination	26.6°
Period	589.2 min
Launch vehicle
Launch site	Cape Canaveral
End of life

Decay	1 Aug 1977


 LES 5

General

Designation	02866 / 67066E
Launch date	1 Jul 1967
Country of origin	United States
Mission	Military: ?
Perigee/Apogee	33188/33618 km
Inclination	11.6°
Period	1316.1 min
Launch vehicle
Launch site	Cape Canaveral

Could be equipped with a SNAP generator?


 LES 6

General

Designation	03431 / 68081D
Launch date	26 Sep 1968
Country of origin	United States
Mission	Military: telecommunications
Geostationary orbit
Launch vehicle
Launch site	Cape Canaveral
End of life

Out of service	yes

Could be equipped with a SNAP generator?


 LES 8

General

Designation	08746 / 76023A
Launch date	15 Mar 1976
Country of origin	United States
Mission	Military: telecommunications
Geostationary orbit	see below
Launch vehicle	Titan 3 C
Launch site	Cape Canaveral
Mass at launch	450 kg

LES 8 & 9 were placed in geostationary orbit with 90° between each other. Equipped with a radio isotropic 238 plutonium generator, they could communicate without the help of a ground station.

Location

Begin	End	Position
L: 15 Mar 1976		?
Mar 1995		94.5°W, inclined
Jan 1996		103°W, inclined


 LES 9

General

Designation	08747 / 76023B
Launch date	15 Mar 1976
Country of origin	United States
Mission	Military: telecommunications
Geostationary orbit	see below
Launch vehicle	Titan 3 C
Launch site	Cape Canaveral
Mass at launch	450 kg

LES 8 & 9 were placed in geostationary orbit with 90° between each other. Equipped with a radio isotropic 238 plutonium generator, they could communicate without the help of a ground station.

Location

Begin	End	Position
L: 15 Mar 1976		?
Mar 1995		105.5°W, inclined
Jan 1996		105°W, inclined


 Program: Loral DBS

2 satellites planned to provide digital services

32 Ku-band transponders at 110 W and 24 transponders at 20 W


 Program: Luch

Means "beam"; also called Al'tair or SDRN

Russian program for LEO communications relay (e.g. Mir). This program is also known as SDRN (Satellite Data Relay Network).

The first generation satellites of this program were based on the Al'tair platform. The second generation performance is said to increase the capacity of the channels by nearly 3 and its lifetime would be twice as long.


Program: Luch

Cosmos 1700

Cosmos 1897

Cosmos 2054

Luch 0

Luch 1


Luch's specifications

Prime contractor	NPOPM
Platform	Al'tair
Mass at launch	2000 kg
Dimension	8.5 x 11 x 16 m
Stabilization	3 axis, 0.5° GEO precision
DC power	1800 W
Design lifetime	5 years
UHF-band (0.9/0.7 GHz)

Main transponders	1
Coverage	6° spotbeam
EIRP	40.7 dBW
Ku-band - data

Main transponders	1
Coverage	0.5° spotbeam
EIRP	55.2 dBW
Uplink	14.591-14.625 GHz LHCP
Downlink	13.511-13.545 GHz RHCP
Ku-band

Main transponders	1
Coverage	1° spotbeam
EIRP	42.3 dBW
Uplink	15.130-15.180 GHz LHCP
Downlink	10.810-10.860 GHz RHCP


 Luch 0

General

Designation	23426 / 94082A
Launch date	16 Dec 1994 at 12:00 UT
Country of origin	CIS
Mission	Telecommunications
Geostationary orbit	95°E
Launch vehicle	Proton #230
Mass at launch	2000 kg

Transmits data to and from Mir station. It is equipped with a Cospas payload.

Technical data

Specifications


 Luch 1

General

Designation	23680 / 95054A
Launch date	11 Oct 1995 at 16:26 UT
Country of origin	CIS
Mission	Telecommunications
Geostationary orbit	77°E
Launch vehicle	Proton #236
Mass at launch	2400 kg

Equipped with a Cospas payload?

Its performance is said to increase the capacity of the channels by nearly 3 and its service lifetime would be twice as long compared to the Al'tair design.


 Lusat

Also called Microsat 4 or LO-19 or Oscar 19

General

Designation	20442 / 90005G
Launch date	22 Jan 1990
Country of origin	Argentina
Mission	Telecommunications
Perigee/Apogee	779/797 km
Inclination	98.6°
Period	100.6 min
Launch vehicle	Ariane V35
Mass at launch	9 kg

Based on an Amsat-NA Microsat bus

Technical data

Passive stabilization

Uplink	1200 bps Manchester coded (Biphase-L) FSK (FM) AX.25 145.840 145.860 145.880 145.900 MHz
Downlink	1200 bps BPSK (SSB) AX.25, either one of the two frequencies below: 437.154 MHz (LHCP in northern hemisphere), normal unfiltered PSK 437.126 MHz (RHCP in northern hemisphere), Raised Cosine modulation
CW beacon	437.126 MHz (when active)


 Program: Mabuhay

Mabuhay Philippines Satellite Inc. (MPSI) is owned by Phillipine Long Distance Telephone Co (PLDT). Partners are Philippines Communications Satellite Corp, Republic Broadcasting System and Cable Entertainment Group.

Phillipine Long Distance Telephones (PLDT) announced they would launch 3 satellite called Mabuhay 1-3 in late 1996-1998. prime contractor: Space Systems/Loral First satellite will have 30 C-band transponders and 4 Ku-band ones Coverage: entire South-East and Pacific Rim

1 satellite is to be launched by LM 3C (or LM 2C?) in early-1997


 Program: Magion

Czech scientific program designed with the Soviets


Program: Magion

Magion 1

Magion 2

Magion 3

Magion 4


 Magion 1

General

Designation	11110 / 78099C
Launch date	24 Oct 1978
Country of origin	Czechoslovakia
Mission	Scientific
Perigee/Apogee	404/762 km
Inclination	83°
Period	96.4 min
Launch vehicle
Launch site	Plesetsk
End of life

Decay	11 Sep 1981


 Magion 2

General

Designation	20281 / 89080B
Launch date	28 Sep 1989
Country of origin	Czechoslovakia
Mission	Scientific: magnetosphere study
Perigee/Apogee	498/2441 km
Inclination	82.6°
Period	115.3 min
Launch vehicle
Launch site	Plesetsk


 Magion 3

General

Designation	21835 / 91086E
Launch date	18 Dec 1991
Country of origin	Czechoslovakia
Mission	Scientific: magnetosphere study
Perigee/Apogee	435/3045 km
Inclination	82.6°
Period	121.3 min
Launch vehicle
Launch site	Plesetsk
Technical data

Downlink frequency: 135.150/137.850 MHz


 Magion 4

General

Designation	23646 / 95039F
Launch date	2 Aug 1995 at 23:59 UT
Country of origin	Czech Republic
Mission	Scientific: magnetosphere study
Perigee/Apogee	760/191760 km
Inclination	63.3°
Period	5454 min
Launch vehicle	Molniya M
Launch site	Plesetsk LC43
Mass at launch	50 kg

It carries instruments to measure electric and magnetic fields for comparison with the Prognoz instruments.


 Program: Marecs

European maritim telecommunication program designed from the Eutelsat platform. Operated by ESA.

Satellites used by Inmarsat


Program: Marecs

Marecs A

Marecs B1

Marecs B2


Marecs's specifications

Prime contractor	British Aerospace (now MMS)
Platform	ECS
Mass at launch	1056 kg
Payload mass	100 kg
Dimension	1.9 x 1.4 x 2.56 m
Solar array	13.9 m span
Stabilization	3 axis
DC power	EOL: 789 W
Design lifetime	7 years
Capacity	50 duplex voice channels


Marecs's L-band

Main transponders	1
Backup transponders	1
Power	50 to 60 W
Bandwidth
Coverage	global
EIRP	35 dBW
Polarization


Marecs's C-band

Main transponders	1
Backup transponders
Power	20 W?
Bandwidth
Coverage	global
EIRP
Polarization


 Marecs A

General

Designation	13010 / 81122A
Launch date	20 Dec 1981
Country of origin	Europe
Mission	Telecommunications
Geostationary orbit	see below
Launch vehicle	Ariane L04
Location

Begin	End	Position
L: 20 Dec 1981		15°W / 26°W
21 Mar 1993		22.8°E, inclined
Technical data

Specifications

L-band

C-band

Transmits on 137.17 MHz


 Marecs B1

End of life

Out of service	10 Sep 1982
Cause	Ariane L05's launch failure
Technical data

Specifications

L-band

C-band


 Marecs B2

General

Designation	15386 / 84114B
Launch date	10 Nov 1984
Country of origin	Europe
Mission	Telecommunications
Geostationary orbit	see below
Launch vehicle	Ariane V11
Location

Begin	End	Position
L: 10 Nov 1984		55°W
21 Mar 1993		14.9°W, inclined
Technical data

Specifications

L-band

C-band


 Program: Marisat

American maritim telecommunication satellite program launched by NASA for Comsat. Were first used by military forces before been used by private companies. Used by Inmarsat.

Contact

COMSAT Corporation

6560 Rock Spring Drive, Bethesda, MD 20817, USA

Tel: +1-301-214-3658

Fax: +1-301-214-7130

http://www.comsat.com


Program: Marisat

Marisat 1

Marisat 2

Marisat 3


 Marisat 1

General

Designation	08697 / 76017A
Launch date	19 Feb 1976
Country of origin	United States
Mission	Telecommunications
Geostationary orbit	see below
Launch vehicle	Thor Delta #120
Location

Begin	End	Position
L: 19 Feb 1976		105°W
Mar 1995		106°W, inclined
Technical data

Transmits in P-, L- and C-band


 Marisat 2

General

Designation	08882 / 76053A
Launch date	10 Jun 1976
Country of origin	United States
Mission	Telecommunications
Geostationary orbit	see below
Launch vehicle	Thor Delta #124
Location

Begin	End	Position
L: 10 Jun 1976		73°E
Mar 1995		72.5°E, inclined
Technical data

Transmits in P- (250 MHz), L- (1.537-1.541 GHz) and C-band (4.195-4.199 GHz)

The satellite also uses the military aviation band in the 248.850 and 249.345 MHz (25 KHz raster): 20 channels for voice and data. They are also two 500 KHz channels for wideband transmissions (254.150-257.550 MHz).


 Marisat 3

General

Designation	09478 / 76101A
Launch date	14 Oct 1976
Country of origin	United States
Mission	Telecommunications
Geostationary orbit	see below
Launch vehicle	Thor Delta #127
Location

Begin	End	Position
L: 14 Oct 1976		15°W
Mar 1995		178°W, inclined
Technical data

Transmits in P-, L- and C-band


 Program: MCI

Warning: this is not the official name

DBS satellite system to operate from the 110°W slot (the bid was won with $682.6 million). Operated by the MCI-News corporation venture

The total program including satellites and launch delivered in orbit and uplink facilities is valued between $400 and $500.


Program: MCI

MCI 1

MCI 2


MCI's specifications

Prime contractor	Space Systems/Loral
Platform
Mass at launch
Mass in orbit
Dimension
Solar array
Stabilization
DC power	7500 W
Design lifetime	12 years


MCI's Ku-band

Main transponders	32
Backup transponders
Power
Bandwidth
Coverage	United States, Hawaii, Alaska and Puerto Rico
EIRP
Polarization


 MCI 1

Warning: this is not the official name

General

Designation
Launch date	planned in late 1997
Country of origin	United States
Mission	Telecommunications
Geostationary orbit	110°W
Launch vehicle	Proton
Launch site
Technical data

Specifications

Ku-band


 MCI 2

Warning: this is not the official name

General

Designation
Launch date	planned in early 1998
Country of origin	United States
Mission	Telecommunications
Geostationary orbit	110°W
Launch vehicle	Atlas 2AS
Launch site
Technical data

Specifications

Ku-band


 Program: Measat

Malaysian East Asian Satellite

Telecommunication program operated by Binariang Sdn. Bhd., a 1987 privatized company

Cost of the program: $235 million. Hughes also supplied equipment for a satellite control station on Malaysia's Langkawi Island and trained the Malaysian spacecraft controllers.

Contact

Measat

Binariang Sdn. Bhd., ground floor, 12 Jalan Gelenggang, 50490 Kuala Lumpur, Malaysia

Tel: +60-3-252-2000

Fax: +60-3-252-2535


Program: Measat

Measat 1

Measat 2


 Measat 1

Malaysian East Asia Satellite

General

Designation	23765 / 96002B
Launch date	12 Jan 1996
Country of origin	Malaysia
Mission	Telecommunications
Geostationary orbit	91.5°E
Launch vehicle	Ariane V82
Technical data

Specifications

Prime contractor	Hughes
Platform	HS-376
Mass at launch	1450 kg
Mass in orbit	650 kg
Diameter	2.16 m
Height	7.82 m deployed
Stabilization	Spin stabilized
DC power	BOL: 1705 W EOL: 800 W
Design lifetime	12 years
C-band

Main transponders	12
Backup transponders
Power	12 W (SSPA)
Bandwidth	36 MHz
Coverage	Malaysia, Philippines & South-India
EIRP	39 dBW
Polarization	linear
Frequencies	Uplink: 5.925-6.425 GHz Downlink: 3.700-4200 GHz
Ku-band

Main transponders	4
Backup transponders
Power	112 W (TWTA)
Bandwidth	54 MHz
Coverage	narrow spot: Malaysia or Philippines or South-India (transponders individullay switchable)
EIRP	57 dBW
Polarization	linear
Frequencies	Uplink: 14.000-14.250 GHz Downlink: 10.950-11.200 GHz
Ku-band transponder frequency chart (GHz)

Transponder	Polarization	Frequency
1		10.982
2		11.044
3		11.106
4		11.168


Measat 1's C-band EIRP


 Measat 2

General

Designation
Launch date	planned in Oct 1996
Country of origin	Malaysia
Mission	Telecommunications
Geostationary orbit	95°E
Launch vehicle	Ariane
Technical data

Built by Hughes, 6 powerful Ku-band transponders and 10 C-band transponders

Ku-band: switchable (by transponder) to: Malaysia, Queensland/Australia, Indonesia and Vietnam (+Singapore)

1500 kg at launch time


 Meteor (US)

General

Designation	n/a
Launch date	23 Oct 1995
Country of origin	United States
Mission	Scientific: Microgravity
Perigee/Apogee	n/a
Inclination	n/a
Period	n/a
Launch vehicle	Conestoga #01
Mass at launch	~1000 kg

The satellite was a commercial microgravity recoverable spacecraft operated by EER Systems. Equipped with a Star 48 solid motor

The loss is amounted $20 million for the launcher and at least $73 million for the experiments

3 commercial experiments onboard:  an atomic-oxygen experiment from S-Cubed, a concentrator solar array from Able Engineering, and a Motorola payload whose details are unrevealed.

End of life

Out of service	23 Oct 1995
Cause	Launcher failed


 Program: Meteor

Soviet meteorology satellite program. Mission: met observation: clouds, ice cover and atmospheric radiation; high speed natural phenomena: cyclone, tidal action, dust storms, etc.

Meteor 1 series

30/31 satellites launched

Meteor 2 series

21 satellites launched

Meteor 3 series

6 since 1985


Program: Meteor

Meteor-Cosmos

Cosmos 0122	Cosmos 0144	Cosmos 0156	Cosmos 0184	Cosmos 0206
Cosmos 0226
Meteor 1

Meteor 1-01	Meteor 1-02
Meteor 2

Meteor 2-01	Meteor 2-21
Meteor 3

Meteor 3-03	Meteor 3-05	Meteor 3-06


Meteor-Cosmos' specifications

Prime contractor
Mass at launch	2000 kg
Diameter	1.5 m?
Height	5 m?
Solar array	2 solar panels
Stabilization	3 axis?


Meteor 1's specifications

Prime contractor
Mass at launch	2200 kg
Diameter	1.5 m?
Height	5 m?
Solar array	2 solar panels
Stabilization	3 axis?


Meteor 2's specifications

Prime contractor	VNII Elektromekaniki
Mass in orbit	1500 kg
Diameter	2 m
Height	5 m
Solar array	2 panels of 10 m
Stabilization	3 axis


Meteor 2's payload

Scanning Telephotometer (direct imaging)

Wavebands	0.5-7.0 µm (visible)
Resolution	global coverage: 2 km regional coverage: 1 km
Scanning IR Radiometer

Wavebands	8-12 µm (IR)
Resolution	global coverage: 8 km
Scanning IR Spectrometer

Wavelengths	11, 10-18, 70 µm (IR)
Resolution	30 km


Meteor 3's specifications

Prime contractor	VNII Elektromekaniki
Mass in orbit	1500 kg
Diameter	2 m
Height	5 m
Solar array	2 panels of 10 m
Stabilization	3 axis


Meteor 3's payload

Scanning Telephotometer (direct imaging)

Wavebands	0.5-7.0 µm (visible)
Resolution	global coverage: 2 km regional coverage: 1 km
Scanning IR Radiometer

Wavebands	8-12 µm (IR)
Resolution	global coverage: 8 km
Scanning IR Spectrometer

Wavelengths	11, 10-18, 70 µm (IR)
Resolution	30 km

+TOMS (Total Ozone mapping Spectrometer): provided by the United States


 Meteor 1-01

General

Designation	03835 / 69029A
Launch date	26 Mar 1969
Country of origin	CIS
Mission	Meteorology
Perigee/Apogee	548/575 km
Inclination	81.2°
Period	95.9 min
Launch vehicle
Launch site	Plesetsk
Mass at launch	2200 kg
Technical data

Specifications


 Meteor 1-02

General

Designation	04119 / 69084A
Launch date	6 Oct 1969
Country of origin	CIS
Mission	Meteorology
Perigee/Apogee	514/550 km
Inclination	81.2°
Period	95.3 min
Launch vehicle
Launch site	Plestesk
Technical data

Specifications


 Meteor 2-01

General

Designation	08026 / 75064A
Launch date	11 Jul 1975
Country of origin	CIS
Mission	Meteorology
Perigee/Apogee	844/876 km
Inclination	81.3°
Period	102.2 min
Launch vehicle
Launch site	Plesetsk
Technical data

Specifications

Payload


 Meteor 2-21

General

Designation	22782 / 93055A
Launch date	31 Aug 1993 at 04:40 UT
Country of origin	CIS
Mission	Meteorology
Perigee/Apogee	934/966 km
Inclination	82.5°
Period	104.1 min
Launch vehicle	Cyclone
Launch site	Plesetsk LC32
Technical data

Specifications

Payload


 Meteor 3-03

General

Designation	20305 / 89086A
Launch date	24 Oct 1989
Country of origin	CIS
Mission	Meteorology
Perigee/Apogee	1235/1248 km
Inclination	82.6°
Period	110.3 min
Launch vehicle
Launch site	Plesetsk
End of life

Out of service	yes
Technical data

Specifications

Payload

APT downlink frequency: 137.300 MHz (current status unknown)


 Meteor 3-05

General

Designation	21655 / 91056A
Launch date	15 Aug 1991
Country of origin	CIS
Mission	Meteorology
Perigee/Apogee	1184/1203 km
Inclination	82.55°
Period	109.3 min
Launch vehicle
Launch site	Plesetsk
Technical data

Transmits on 137.85 MHz


 Meteor 3-06

General

Designation	22969 / 94003A
Launch date	25 Jan 1994
Country of origin	CIS
Mission	Meteorology
Perigee/Apogee	1184/1209 km
Inclination	82.55°
Period	109.36 min
Launch vehicle	Cyclone
Launch site	Plesetsk

On board was a German PRARE navigational system to measure parameters of spacecraft motion.

The French Scarab payload for radiation budget failed in April 1995. This instrument will fly again in late-1996 and on Envisat.

Technical data

Specifications

Payload


 Program: Meteosat

A series of meteorological satellites operated by Eumetsat. The satellites observe cloud formation across the full Earth disk and generate images in 3 spectral bands every 30 minutes.

Mission: observation of cloud cover, windspeeds, sea and cloud surface temperature, water vapor distribution in upper troposphere. Images acquisition, distribution of image data and other met info, collection and relay of weather data from data collection platforms (DCPs) - and, sea and airborne.

The 3 first satellites are experimental, the 3 next are operational: MOP (Meteosat OPerational). Then the program will use MTP (Meteosat Transition Program) and finally MSG (Meteosat Second Generation).

The satellites are owned by Eumetsat (European Meteorologic Satellite), an organization created in May 1983 based at Darmstadt, Germany that counts 17 members: Austria, Belgium, Denmark, Finland, France, Germany, Greece, Ireland, Italy, Netherlands, Norway, Portugal, Spain, Sweden, Switzerland, Turkey and United Kingdom.

Funding: $4.5 million (1985-1995); Germany 24%, France 18%, Italy 15% and UK 14%

Contact

EUMETSAT

Am Elfengrund 45

D-64297 Darmstadt

Germany

Tel: +49-6151-950-0

Fax: +49-6151-950125


Program: Meteosat

Meteosat 1

Meteosat 2

Meteosat 3

Meteosat 4

Meteosat 5

Meteosat 6

Meteosat 7

MSG


Meteosat 4, 5, 6's specifications

Prime contractor	Aerospatiale
Mass at launch	681 kg
Mass in orbit	316 kg
Diameter	2.1 m
Height	3.1 m
Stabilization	Spin stabilized (100 rpm)
DC power	BOL: 387 W EOL: 225 W
Design lifetime	5 years


Meteosat 4, 5, 6's payload

Multispectral Radiometer

Wavebands	0.4-1.1 µm (visible) 5.7-7.1 µm (IR): water vapor absorption 10.5-12.5 µm (thermal IR)
Resolution	visible: 2.5 km others: 5 km
Image repeat frequency	30 minutes (3 bands)
Telemetry - Data	UHF- and S-band (1 transponder per band)
Data rate	333 kbps (normal), 2.7 Mbps (burst)
MMD (Meteorological Data Dissemination)

Channel frequencies	digital high resolution (HR): 1694.5 MHz analogue weather facsimile (WEFAX): 1691 MHz
MDD (A & B)	1.695.77 +/- 0.165 MHz


 Meteosat 1

General

Designation	10489 / 77108A
Launch date	23 Nov 1977
Country of origin	Europe
Mission	Meteorology
Geostationary orbit
Launch vehicle	Thor Delta #136
Mass at launch	700 kg
End of life

Out of service	Oct 1984


 Meteosat 2

General

Designation	12544 / 81057A
Launch date	19 Jun 1981
Country of origin	Europe
Mission	Meteorology
Geostationary orbit
Launch vehicle	Ariane L03

Has provided 284000 images

End of life

Out of service	6 Dec 1991 to the junk orbit (36119/36334 km)


 Meteosat 3

General

Designation	19215 / 88051A
Launch date	15 Jun 1988
Country of origin	Europe
Mission	Meteorology
Geostationary orbit	see below
Launch vehicle	Ariane V23
Location

Begin	End	Position
L: 15 Jun 1988	Jun 1989	0°E
Jun 1989	Jan 1990	50°W
Jan 1990	Apr 1990	0°E
Apr 1990	?Nov 1990	5°W
Jul 1991		50°W
late 1992		75°W
Apr 1993		72.8°W
Feb 1995	Nov 1995	70°W, inclined

In May 1995 Eumetsat decided it didn't need the satellite back so it remained in reserve around 70°W before final burn.

End of life

Out of service	mid Nov 1995
Cause	pushed to the junk orbit
Technical data

Downlink frequency: 137.08 & 1691 MHz + in S-band


 Meteosat 4

Also called MOP 1

General

Designation	19876 / 89020B
Launch date	6 Mar 1989
Country of origin	Europe
Mission	Meteorology
Geostationary orbit	see below
Launch vehicle	Ariane V29

First operational satellite

Location

Begin	End	Position
L: 6 Mar 1989		0°E
Feb 1995	May 1995	7.7°W
Aug 1995	Oct 1995	10°E, inclined
End of life

Out of service	Early Nov 1995
Cause	pushed to the junk orbit
Technical data

Specifications

Payload

Downlink frequency: 137.08 MHz, 1691 & 1694.5 MHz + in S-band


 Meteosat 5

Also called MOP 2

General

Designation	21140 / 91015B
Launch date	2 Mar 1991
Country of origin	Europe
Mission	Meteorology
Geostationary orbit	see below
Launch vehicle	Ariane V42
Location

Begin	End	Position
L: 2 Mar 1991		0°E
Feb 1995	...	1°W
Technical data

Specifications

Payload

Downlink frequency: 137.08 MHz, 1691 & 1694.5 MHz + in S-band


 Meteosat 6

Also called MOP 3

General

Designation	22912 / 93073B
Launch date	20 Nov 1993
Country of origin	Europe
Mission	Meteorology
Geostationary orbit	see below
Launch vehicle	Ariane V61

The radiometer didn't work in IR band thus temperature couldn't be measured. The problem could be solved in April 1995 after a software was developped to correct the data.

Cost: $67.5 million

Location

Begin	End	Position
L: 20 Nov 1993		9.5°W
Technical data

Specifications

Payload

Downlink frequency: 137.08 MHz, 1691 & 1694.5 MHz

Equipped with 1 S-band transponder. Data rate: 2.6 Mbps


 Meteosat 7

Also called MTP 1

planned for June 1997, launched by Ariane

part of MTP (Meteosat Transitional Program)


Program: MSG
 Program: Meteosat Second Generation (MSG)

3 satellites are to be launched by Ariane in 2000, 2002 and 2006 by Ariane 5

The first MSG is being developed within the scope of a European Space Agency (ESA) program, with Aerospatiale of France acting as prime contractor and financing by Eumetsat.

12 channels, 15 min image repeat, lifetime: 7 years


 Microlab 1

General

Designation	23547 / 95017C
Launch date	3 Apr 1995 at 13:48 UT
Country of origin	United States
Operator	Orbital Science Corporation
Mission	Scientific
Perigee/Apogee	727/756 km
Inclination	70°
Period
Launch vehicle	Pegasus #8
Launch site	Cape Canaveral

It carries NASA-MSFC's Optical Transient Detector experiment to study the global distribution of lightning, and the University Corporation for Atmospheric Research's GPS-MET experiment which will study the occultation of GPS navigation satellite signals by the atmosphere to derive meteorological information.

Microlab is owned by OSC, with NASA and NSF renting the space for and operation of their experiments.

Technical data

Specifications

Prime contractor	OSC
Platform	Microstar
Mass at launch	68 kg
Mass in orbit
Diameter	1 m
Height	0.3 m
Stabilization
DC power
Design lifetime


 Program: Midas

MIssile Defense Alarm System

American military satellites for missile launch warning. Equipped with IR detectors and TV cameras.


Program: Midas

Midas 02

Midas 03

Midas 04

Midas 05

Midas 06

Midas 07

Midas 08

Midas 09

Midas 10


 Midas 02

Also called LASP (Low Altitude Surveillance Platform)

General

Designation	00043 / 60006A
Launch date	24 May 1960
Country of origin	United States
Mission	Military: early warning
Perigee/Apogee	473/494 km
Inclination	33°
Period	94.3 min
Launch vehicle	Atlas Agena A
Launch site	Cape Canaveral
End of life

Decay	7 Feb 1974


 Midas 03

General

Designation	00163 / 61018A
Launch date	12 Jul 1961
Country of origin	United States
Mission	Military: early warning
Perigee/Apogee	3342/3541 km
Inclination	91.2°
Period	161.4 min
Launch vehicle	Atlas Agena B
Launch site	Vandenberg


 Midas 04

General

Designation	00192 / 61028A
Launch date	21 Oct 1961
Country of origin	United States
Mission	Military: early warning
Perigee/Apogee	3482/3763 km
Inclination	95.9°
Period	165.9 min
Launch vehicle	Atlas Agena B
Launch site	Vandenberg


 Midas 05

Also called Strongback

General

Designation	00271 / 62010A
Launch date	9 Apr 1962
Country of origin	United States
Mission	Military: early warning
Perigee/Apogee	2784/3405 km
Inclination	86.7°
Period	152.9 min
Launch vehicle	Atlas Agena B
Launch site	Vandenberg


 Midas 06

Also called FTV 1169

General

Designation	00574 / 63014A
Launch date	9 May 1963
Country of origin	United States
Mission	Military: early warning
Perigee/Apogee	3607/3676 km
Inclination	87.3°
Period	166.4 min
Launch vehicle	Atlas Agena B
Launch site	Vandenberg


 Midas 07

Also called ERS 10 or FTV

General

Designation	00622 / 63030A
Launch date	18 Jul 1963
Country of origin	United States
Mission	Military: early warning
Perigee/Apogee	3672/3725 km
Inclination	88.4°
Period	167.8 min
Launch vehicle	Atlas Agena B
Launch site	Vandenberg


 Midas 08

Also called OPS 1960

General

Designation	02200 / 66051A
Launch date	9 Jun 1966
Country of origin	United States
Mission	Military: early warning
Perigee/Apogee	154/3678 km
Inclination	90°
Period	125.2 min
Launch vehicle	Atlas Agena D
Launch site	Vandenberg


 Midas 09

Also called OPS 0856

General

Designation	02403 / 66077A
Launch date	19 Aug 1966
Country of origin	United States
Mission	Military: early warning
Perigee/Apogee	3658/3708 km
Inclination	89.7°
Period	167.4 min
Launch vehicle	Atlas Agena D
Launch site	Vandenberg


 Midas 10

Also called OPS 1920

General

Designation	02481 / 66089A
Launch date	5 Oct 1966
Country of origin	United States
Mission	Military: early warning
Perigee/Apogee	3656/3721 km
Inclination	90°
Period	167.5 min
Launch vehicle	Atlas Agena D
Launch site	Vandenberg


 Miranda

Also called X4

General

Designation	07213 / 74013A
Launch date	9 Mar 1974
Country of origin	United Kingdom
Mission	Technology experimentation
Perigee/Apogee	677/865 km
Inclination	97.9°
Period	100.3 min
Launch vehicle	Scout #86
Mass at launch	93 kg

Built and operated by the RAE. Tested a stabilization system, solar panels and cells


 Mika

General

Designation	04345 / 70017B
Launch date	10 Mar 1970
Country of origin	France
Mission
Perigee/Apogee	302/1180 km
Inclination	5.4°
Period	99.6 min
Launch vehicle	Diamant #5

First launch from Kourou

End of life

Decay	9 Sep 1974


 Program: Molniya

Means "flash of lightning" in Russian

Soviet telecomunication program. Satellites are placed on very excentric orbits (460/40000 km, inclination: 45°) with a 12 hours period. Such satellites remain almost 8 hours above the CIS, slowly drifting high in the sky.

Molniya satellites are used by the Orbita network equipped with 12 m antennas. Mars transportable stations could also use the network with 7 m antennas. Mission: provide long distance reliable telephone and TV links. Molniya-1 are used for government and military communications whereas Molniya-3 are used for TV programs.

As the first Molniya-2 satellites were launched the system became available for Intersputnik. The first satellite operated at 1.0/0.8 GHz. C-band (6/4 GHz) was introduced from Molniya 1-07 on. Satellites also use L-band.

In the future, the system could be replaced by Mayak


Program: Molniya

Molniya 1-01	Molniya 1-71	Molniya 1-72	Molniya 1-74
Molniya 1-85	Molniya 1-86	Molniya 1-87	Molniya 1-88
Molniya 2-01
Molniya 3-01	Molniya 3-34	Molniya 3-35	Molniya 3-36
Molniya 3-37	Molniya 3-42	Molniya 3-44	Molniya 3-45
Molniya 3-46	Molniya 3-47
Molniya 1-S


 Molniya 1-01

General

Designation	01324 / 65030A
Launch date	23 Apr 1965
Country of origin	CIS
Mission	Telecommunications
Perigee/Apogee	538/39300 km
Inclination	65.5°
Period	707.3 min
Launch vehicle
Launch site	Tyuratam
End of life

Decay	16 Aug 1979
Technical data

Specifications

Prime contractor
Platform
Mass at launch	1000 kg
Mass in orbit
Length
Width
Height
Stabilization	Spin?
DC power
Design lifetime
Transmission (upload: 0.8 GHz, download: 1 GHz)

Main transponders	3
Backup transponders
Power	40 W
Bandwidth	240 phone circuits
Coverage
EIRP
Polarization


 Molniya 1-71

General

Designation	18946 / 88017A
Launch date	11 Mar 1988
Country of origin	CIS
Mission	Telecommunications
Perigee/Apogee	491/38976 km
Inclination	62.5°
Period	699 min
Launch vehicle
Launch site	Tyuratam


 Molniya 1-72

General

Designation	18980 / 88022A
Launch date	17 Mar 1988
Country of origin	CIS
Mission	Telecommunications
Perigee/Apogee	655/40584 km
Inclination	62.9°
Period	735 min
Launch vehicle
Launch site	Plesetsk


 Molniya 1-74

General

Designation	19730 / 88115A
Launch date	28 Dec 1988
Country of origin	CIS
Mission	Telecommunications
Perigee/Apogee	654/38870 km
Inclination	62.8°
Period	700 min
Launch vehicle	Molniya
Launch site	Plesetsk


 Molniya 1-85

General

Designation	22309 / 93002A
Launch date	12 Jan 1993
Country of origin	CIS
Mission	Telecommunications
Perigee/Apogee	528/39822 km
Inclination	63.4°
Period	717.7 min
Launch vehicle	Molniya
Launch site	Plesetsk


 Molniya 1-86

General

Designation	22671 / 93035A
Launch date	26 May 1993
Country of origin	CIS
Mission	Telecommunications
Perigee/Apogee	681/39672 km
Inclination	62.9°
Period	717.8 min
Launch vehicle	Molniya
Launch site	Plesetsk


 Molniya 1-87

General

Designation	22949 / 93079A
Launch date	22 Dec 1993
Country of origin	CIS
Mission	Telecommunications
Perigee/Apogee	446/39206 km
Inclination	62.8°
Period	703 min
Launch vehicle	Molniya
Launch site	Plesetsk

Molniya 1-T


 Molniya 1-88

General

Designation	23420 / 94081A
Launch date	14 Dec 1994
Country of origin	CIS
Mission	Telecommunications
Perigee/Apogee	516/39833 km
Inclination	62.8°
Period	718 min
Launch vehicle	Molniya M
Launch site	Plesetsk LC43

Molniya 1-T


 Molniya 2-01

General

Designation	05620 / 71100A
Launch date	25 Nov 1971
Country of origin	CIS
Mission	Telecommunications
Perigee/Apogee	516/39553 km
Inclination	65°
Period	712 min
Launch vehicle
Launch site	Plesetsk
End of life

Decay	10 May 1976


 Molniya 3-01

General

Designation	07540 / 74092A
Launch date	21 Nov 1974
Country of origin	CIS
Mission	Telecommunications
Perigee/Apogee	250/40095 km
Inclination	64.1°
Period	717.6 min
Launch vehicle
Launch site	Plesetsk
Mass at launch	1600 kg
End of life

Decay	15 May 1986


 Molniya 3-34

General

Designation	19713 / 88112A
Launch date	22 Dec 1988
Country of origin	CIS
Mission	Telecommunications
Perigee/Apogee	899/39481 km
Inclination	63.9°
Period	718.3 min
Launch vehicle	Molniya
Launch site	Plesetsk


 Molniya 3-35

General

Designation	20052 / 89043A
Launch date	8 Jun 1989
Country of origin	CIS
Mission	Telecommunications
Perigee/Apogee	1436/38918 km
Inclination	64.8°
Period	717.8 min
Launch vehicle	Molniya
Launch site	Plesetsk


 Molniya 3-36

General

Designation	20338 / 89094A
Launch date	28 Nov 1989
Country of origin	CIS
Mission	Telecommunications
Perigee/Apogee	698/39655 km
Inclination	64.8°
Period	717.8 min
Launch vehicle	Molniya
Launch site	Plesetsk


 Molniya 3-37

General

Designation	20444 / 90006A
Launch date	23 Jan 1990
Country of origin	CIS
Mission	Telecommunications
Perigee/Apogee	982/39367 km
Inclination	64.9°
Period	717.7 min
Launch vehicle
Launch site	Plesetsk


 Molniya 3-42

General

Designation	22178 / 92067A
Launch date	14 Oct 1992
Country of origin	CIS
Mission	Telecommunications
Perigee/Apogee	466/39103 km
Inclination	62.9°
Period	701 min
Launch vehicle
Launch site	Plesetsk


 Molniya 3-44

General

Designation	22633 / 93025A
Launch date	21 Apr 1993 at 00:30 UT
Country of origin	CIS
Mission	Telecommunications
Perigee/Apogee	744/39603 km
Inclination	62.9°
Period	717.7 min
Launch vehicle	Molniya
Launch site	Plesetsk


 Molniya 3-45

General

Designation	22729 / 93049A
Launch date	4 Aug 1993 at 00:52 UT
Country of origin	CIS
Mission	Telecommunications
Perigee/Apogee	511/39841 km
Inclination	62.8°
Period	717.7 min
Launch vehicle	Molniya
Launch site	Plesetsk


 Molniya 3-46

General

Designation	23211 / 94051A
Launch date	23 Aug 1994 at 14:31 UT
Country of origin	CIS
Mission	Telecommunications
Perigee/Apogee	622/39726 km
Inclination	63°
Period	618 min
Launch vehicle	Molniya M
Launch site	Plesetsk


 Molniya 3-47

General

Designation	23642 / 95042A
Launch date	9 Aug 1995 at 01:21 UT
Country of origin	CIS
Mission	Telecommunications
Perigee/Apogee	472/40851 km
Inclination	62.3°
Period
Launch vehicle	Molniya M
Launch site	Plesetsk LC43


 Molniya 1-S

General

Designation	07392 / 74060A
Launch date	29 Jul 1974
Country of origin	CIS
Mission	Telecommunications
Geostationary orbit
Launch vehicle	Proton #49
End of life

Out of service	yes


 Program: Momo

Means "peach tree"

Also called MOS (Marine Observation Satellite)

Japanese remote sensing program. Mission: observethe oceans and marine/land phenomena, measure sea surface temperature and color, suspended sediment, stratospheric water vapor, ice and snow, vegetation characteristics and land use, geology, cartography, environmental monitoring, oceanography, etc.

Orbital cycle: 17 days (237 periods)


Program: Momo

Momo 1A

Momo 1B


Momo's specifications

Prime contractor	NEC
Mass at launch	740 kg
Dimension	1.26 x 1.48 x 2.4 m
Solar array	asymmetric, 2 x 5.3 m
Stabilization	3 axis
Design lifetime	2 years


Momo's payload

MESSR (Multispectral Electronic Self-Scanning Radiometer)

Wavebands	0.51-0.59 µm (visible): water body mapping 0.61-0.69 µm (visible): vegetation differentiation 0.72-0.80 µm (near IR): imaging through haze 0.80-1.10 µm (near IR): land/water separation
Resolution	50 m
Swath width	100 km
VTIR (Visible and Thermal IR Radiometer)

Wavebands	0.50-0.70 µm (visible): snow. ice and cloud 6-7 µm (water vapor band): upper atmosphere water vapor, cirrus 10.5-11.5 µm (thermal IR): ocean currents. sea surface temperature, snow 10.5-12.5 µm (thermal IR): ocean currents. sea surface temperature, snow
Resolution	visible: 0.9 km; others: 2.7 km
Swath width	1500 km
MSR (Microwave Scanning Radiometer)

Wavebands	23.8 +/- 0.2 GHz: water vapor, rain and snowfall 31.4 +/- 0.25 GHz: ice, cloud, snowfall
Resolution	32 km in 23 GHz and 23 in 31 GHz
Swath width	317 km


 Momo 1A

Also called MOS 1A

General

Designation	17527 / 87018A
Launch date	19 Feb 1987
Country of origin	Japan
Mission	Remote sensing
Perigee/Apogee	907/909 km
Inclination	99°
Period	103.2 min
Launch vehicle	N2
Launch site	Tanegashima
Technical data

Specifications

Payload

Downlink frequency: 136.12 MHz


 Momo 1B

Also called MOS 1B

General

Designation	20478 / 90013A
Launch date	7 Feb 1990
Country of origin	Japan
Mission	Remote sensing
Perigee/Apogee	907/909 km
Inclination	99°
Period	103.2 min
Launch vehicle
Launch site	Tanegashima
Technical data

Specifications

Payload

Downlink frequency: 136.12 MHz


 Program: Morelos

Mexican telecommunication program operated by the Secretaria de Communicaciones y Transportes (SCT). The program has been replaced by Solidaridad.


Program: Morelos

Morelos 1

Morelos 2


Morelos's specifications

Prime contractor	Hughes
Platform	HS-376
Mass at launch	1140 kg
Mass in orbit	666 kg
Diameter	2.16 m
Height	6.6 m deployed
Stabilization	Spin stabilized
DC power	BOL: 940 W
Design lifetime	10 years


Morelos's C-band

Main transponders	12+6
Backup transponders	4+2
Power	(6+2) transponders of 72 MHz: 10.5 W (TWTA) (12+4) transponders of 36 MHz: 7.5 W (TWTA)
Bandwidth	(6+2) transponders of 72 MHz (12+4) transponders of 36 MHz
Coverage	Mexico
EIRP	39 dBW
Polarization	linear


Morelos's Ku-band

Main transponders	4
Backup transponders	2
Power	20 W (TWTA)
Bandwidth	108 MHz
Coverage	Mexico
EIRP	44 dBW
Polarization	linear H


Morelos' C-band transponder frequency chart
 Morelos' C-band transponder frequency chart (GHz)

Horizontal Uplink	Horizontal Downlink	Transponder	Channel	Vertical Downlink	Vertical Uplink
	3.720	1W/L	1		5.945
5.965		1N	2	3.740
	3.760	1W/U	3		5.985
6.005		2N	4	3.780
	3.800	3W/L	5		6.025
6.045		3N	6	3.820
	3.840	2W/U	7		6.065
6.085		4N	8	3.860
	3.880	3W/L	9		6.105
6.125		5N	10	3.900
	3.920	3W/U	11		6.145
6.125		6N	12	3.940
	3.960	4W/L	13		6.185
6.205		7N	14	3.980
	4.000	4W/U	15		6.225
6.245		8N	16	4.020
	4.040	5W/L	17		6.265
6.285		9N	18	4.060
	4.080	5W/U	19		6.305
6.325		10N	20	4.100
	4.120	6W/L	21		6.345
6.365		11N	22	4.140
	4.160	6W/U	23		6.385
6.405		12N	24	4.180


Morelos' Ku-band transponder frequency chart (GHz)

Horizontal Uplink	Horizontal Downlink	Transponder	Vertical Downlink	Vertical Uplink
	11.764	1K		14.064
	11.888	2K		14.188
	12.012	3K		14.312
	12.136	4K		14.436


 Morelos 1

General

Designation	15824 / 85048B
Launch date	17 Jun 1985
Country of origin	Mexico
Mission	Telecommunications
Geostationary orbit	113.5°W
Launch vehicle	STS 25
End of life

Out of service	yes
Technical data

Specifications

C-band

Ku-band

C-band transponder frequency chart

Ku-band transponder frequency chart


 Morelos 2

General

Designation	16274 / 85109B
Launch date	27 Nov 1985
Country of origin	Mexico
Mission	Telecommunications
Geostationary orbit	116.8°W
Launch vehicle	STS 31
Technical data

Specifications

C-band

Ku-band

C-band transponder frequency chart

Ku-band transponder frequency chart


 MSTI 1

Miniature Seeker Technology Integration

General

Designation	22229 / 92078A
Launch date	21 Nov 1992 at 13:45 UT
Country of origin	United States
Mission	Technology experimentation
Perigee/Apogee	289/366 km
Inclination	96.7°
Period	91.1 min
Launch vehicle	Scout #116
Mass at launch	135 kg

Designed to test instruments for star war. Two other satellites should be launched.

Cost of the 3 satellites: $19 million


 MSTI 2

Miniature Sensor Technology Integration

General

Designation	23101 / 94028A
Launch date	9 May 1994 at 02:47 UT
Country of origin	United States
Mission	Technology
Perigee/Apogee	411/427 km
Inclination	97.1°
Period	92.9 min
Launch vehicle	Scout #118
Mass at launch	135 kg

It was the last of the now discontinued Scout series. During an orbit it successfully spotted and locked onto a test rocket launched from Edwards AFB.

Operated by the Ballistic Missile Defense Organization


 MSX

Middlecourse Space Experiment

General

Designation
Launch date	planned in Apr 1996
Country of origin	United States
Mission
Perigee/Apogee
Inclination
Period
Launch vehicle	Delta 2
Launch site

Data collection experiment which will concentrate on the phenomena of target detection and tracking. To acquire, track and collect passive infra-red visible and ultraviolet data on a set of objects deployed at midcourse from cooperatively launched ICBM's and sounding rockets.

Contact

http://msx.nrl.navy.mil/


Muses B

[M-5]

More detail on the schedule slip of the M-5. The problem is finding welding cracks in the M-5 motor casings; such a crack is blamed for a rupture in a 1993 pressure test, and both improved materials and improved testing methods have been introduced as a result. The loss of the last M-3S-2 has put ISAS under considerable pressure to make sure the M-5 works properly. Original date for the first launch was mid-1995. It's now mid-1996, and a further six-month slip is likely due to side effects of the Kobe earthquake. ISAS is unhappy that tight funding will restrict static testing.

Meanwhile, development is on track for the first M-5 payloads. The Muses-B VLBI radio-astronomy spacecraft (including a 10m dish antenna) will be ready for launch (into a 620x6200mi elliptical orbit) in mid-1996. The Lunar-A mission, a lunar orbiter carrying three penetrator landers, will be ready for mid-1997 launch. And early testing is underway on the Planet-B spacecraft, a fields-and-particles Mars orbiter, set to fly in winter 1998.


 Program: MTSat

Japanese system for navigation and air regulation. Ordered by the Japanese Ministry for Transport to Space Systems/Loral ($102 million). The first satellite will be launched by H2 in 1999. Possible option for a second satellite in 2004

Possible slots: 135°E, 140°E & 145°E

Would operate in UHF-, L-, S-, Ku- and Ka-band


 Myojo

Also called VEP (Vehicle Evaluation Payload)

General

Designation	22979 / 94007B
Launch date	3 Feb 1994
Country of origin	Japan
Operator	NASDA
Mission	Technology
Perigee/Apogee	430/36114 km
Inclination	29.12°
Period	641.95 min
Launch vehicle	H2 01


 Program: N Star

Japanese telecommunication operated by NTT corp. program that follows the Sakura series.

The satellites will provide inter-orbit links, high quality DBS TV and mobile links. They will enable the use of cellular phones anywhere in Japan (in 1995 the existing cellular phone system covers 95% of Japan's populated areas but does not cover mountainous areas). This service will be provided by NTT's mobile phone unit, NTT Mobile Communications Network Inc.

Designed to replace the Sakura 3A & 3B satellites

Contact

Nippon Telegraph and Telephone Corporation

1-6 Uchisaiwai-cho, 1-chome, Chiyoda-Ku, Tokyo 100, Japan

Tel: +81-3-3509-3101

Fax: +81-3-3509-4290


Program: N Star

N Star a

N Star b


N Star's specifications

Prime contractor	Space Systems/Loral
Platform	FS 1300
Mass at launch	3400 kg
Mass in orbit	2050 kg
Dry mass	1617 kg
Dimension	3.1 x 2.4 x 2.2 m
Solar array	27.3 m
Stabilization	3 axis
DC power	5200 W, nickel-hydrogen batteries
Design lifetime	10 to 12 years


N Star's S-band

Main transponders	4
Backup transponders
Power
Bandwidth
Coverage	Japan, 4 beams
EIRP
Polarization


N Star's C-band

Main transponders	6
Backup transponders
Power	20 W (TWTA)
Bandwidth
Coverage	Japan
EIRP
Polarization


N Star's Ku-band

Main transponders	8
Backup transponders
Power	40 W (TWTA)
Bandwidth
Coverage	Japan
EIRP
Polarization
Frequencies	Downlink: 12.19-12.91 GHz


N Star's Ka-band

Main transponders	11
Backup transponders
Power	20 W (TWTA)
Bandwidth
Coverage	Japan
EIRP
Polarization
Frequencies	Downlink: 17.75-19.45 GHz

For military purposes & switched TDMA service on Ka-band multi-beam


 N Star a

General

Designation	23651 / 95044A
Launch date	29 Aug 1995
Country of origin	Japan
Mission	Telecommunications
Geostationary orbit	132°E
Launch vehicle	Ariane V77

An accident during transportation to the launch site damaged the spacecraft which delayed it. Was delivered in orbit in late October 1995

Technical data

Specifications

S-band

C-band

Ku-band

Ka-band


 N Star b

General

Designation	23781 / 96007A
Launch date	5 Feb 1996
Country of origin	Japan
Mission	Telecommunications
Geostationary orbit	136°E
Launch vehicle	Ariane V83
Technical data

Specifications

S-band

C-band

Ku-band

Ka-band


 Program: Nadezhda

Nadezhda means 'hope'

Russian navigation program using the Tsikada platform. The satellites of this program carry a Cospas receiver.

The Nadezhda M generation (started with Cosmos 2315) carries hardware that can either provide Cospas or Kurs services.

Designed by AO Polyot and NPO PM


Program: Nadezhda

Nadezhda 1

Nadezhda 2

Nadezhda 3

Nadezhda 4


 Nadezhda 1

General

Designation	20103 / 89050A
Launch date	4 Jul 1989
Country of origin	CIS
Mission	Navigation
Perigee/Apogee	954/1011 km
Inclination	83°
Period	104.8 min
Launch vehicle	Cosmos
Launch site	Plesetsk


 Nadezhda 2

General

Designation	20508 / 90017A
Launch date	27 Feb 1990
Country of origin	CIS
Mission	Navigation
Perigee/Apogee	950/1018 km
Inclination	83°
Period	104.8 min
Launch vehicle	Cosmos
Launch site	Plesetsk
Technical data

Used to transmit on 150 & 400 MHz (replaced by Nadezhda 4)


 Nadezhda 3

General

Designation	21152 / 91019A
Launch date	12 Mar 1991
Country of origin	CIS
Mission	Navigation
Perigee/Apogee	952/1015 km
Inclination	82.9°
Period	104.8 min
Launch vehicle
Launch site	Plesetsk
Technical data

Downlink frequencies: 150 & 400 MHz

Plane 12


 Nadezhda 4

General

Designation	23179 / 94041A
Launch date	14 Jul 1994 at 06:13 UT
Country of origin	CIS
Mission	Navigation
Perigee/Apogee	951/1007 km
Inclination	82.9°
Period	104.7 min
Launch vehicle
Launch site	Plesetsk
Technical data

Downlink frequencies: 150 & 400 MHz

Plane 14


 Program: Nahuel

Argentine first telecommunication program operated by Nahuelsat (or paracomsat?)

1 satellite should be launched by Ariane


Program: Nahuel

Nahuel 1


 Nahuel 1

General

Designation
Launch date	1997 or Sep 1996?
Country of origin	Argentina
Mission	Telecommunications
Geostationary orbit	72° West
Launch vehicle	Long March 3C / Ariane (contract with both!)
Launch site
Technical data

Specifications

Prime contractor	Aerospatiale with DASA
Platform	Spacebus 2000
Mass at launch	1820 kg
Mass in orbit
Length
Width
Height
Stabilization
DC power
Design lifetime
Ku-band

Main transponders	18
Backup transponders
Power
Bandwidth	54 MHz
Coverage	Argentina and neighboring countries
EIRP	50 dBW
Polarization

3 beams


 Program: Nato

North Atlantic Treaty Organization

Military communications satellites for the NATO


Program: Nato

Nato 1	Nato 2
Nato 3A	Nato 3B	Nato 3C	Nato 3D
Nato 4A	Nato 4B


Nato 3's specifications

Downlink frequecies	7.2 to 7.5 GHz
Design lifetime	7 years


Nato 4's specifications

Prime contractor	Britsh Aerospace (now MMS)
Platform	ECS
Mass at launch	1430 kg
Payload mass	215 kg
Length	2.2 m
Height	2.3 m
Solar array	16 m span
Stabilization	3 axis
DC power	EOL: 1200 W
Design lifetime	7 years

Based on the design of the Skynet 4 satellites


Nato 4's UHF-band (250-315 MHz)

Main transponders	2 or 4?
Backup transponders
Power	40 W
Bandwidth	25 KHz
Coverage	Europe
EIRP


Nato 4's X-band

Main transponders	4
Backup transponders
Power	40 W
Bandwidth	60 and 135 MHz
Coverage	global
EIRP
Polarization


 Nato 1

General

Designation	04353 / 70021A
Launch date	20 Mar 1970
Country of origin	NATO
Mission	Military: telecommunications
Geostationary orbit
Launch vehicle	Thor Delta #77
End of life

Out of service	yes


 Nato 2

General

Designation	04902 / 71009A
Launch date	3 Feb 1971
Country of origin	NATO
Mission	Military: telecommunications
Geostationary orbit	see below
Launch vehicle	Thor Delta #82
End of life

Out of service	yes


 Nato 3A

General

Designation	08808 / 76035A
Launch date	22 Apr 1976
Country of origin	NATO
Mission	Military: telecommunications
Geostationary orbit	18°W
Launch vehicle	Thor Delta #122
Mass at launch	376 kg
End of life

Out of service	yes
Technical data

Specifications


 Nato 3B

General

Designation	09785 / 77005A
Launch date	28 Jan 1977
Country of origin	NATO
Mission	Military: telecommunications
Geostationary orbit
Launch vehicle	Thor Delta #128
Mass at launch	680 kg
End of life

Out of service	yes
Technical data

Specifications


 Nato 3C

General

Designation	11115 / 78106A
Launch date	19 Nov 1978
Country of origin	NATO
Mission	Military: telecommunications
Geostationary orbit
Launch vehicle	Thor Delta #146
End of life

Out of service	yes
Technical data

Specifications


 Nato 3D

General

Designation	15391 / 84115A
Launch date	14 Nov 1984
Country of origin	NATO
Mission	Military: telecommunications
Geostationary orbit	see below
Launch vehicle	Thor Delta #177
Location

Begin	End	Position
L: 14 Nov 1984
Feb 1995		21°W, inclined

Downlinks in UHF- (250-315 MHz), C- and X-band


 Nato 4A

General

Designation	21047 / 91001A
Launch date	8 Jan 1991
Country of origin	NATO
Mission	Military: telecommunications
Geostationary orbit	18°W, inclined
Launch vehicle	Delta 2 #202
Technical data

Specifications

UHF-band

X-band

Also downlinks in C-band


 Nato 4B

Also called USA 098

General

Designation	22921 / 93076A
Launch date	8 Dec 1993
Country of origin	NATO
Mission	Military: telecommunications
Geostationary orbit	6°E, inclined
Launch vehicle	Delta 2 #224
Technical data

Specifications

UHF-band

X-band

Also downlinks in C-band


 Nilesat 1

General

Designation
Launch date	late 1997
Country of origin	Egypt
Mission	Telecommunications
Geostationary orbit	7°W
Launch vehicle	Ariane
Launch site

On the contract: 2 satellites (1 = ground spare) + 2 earth stations on the contract: total amount: $158 million for Matra Marconi Space

Technical data

Specifications

Prime contractor	Matra Marconi Space
Platform
Mass at launch	1700 kg
Mass in orbit
Dimension
Solar array
Stabilization
DC power
Design lifetime	12 years
Ku-band

Main transponders	12
Backup transponders
Power	100 W
Bandwidth	33 MHz
Coverage	Middle East
EIRP
Polarization

2.3 m diameter onboard antenna


 Program: Nimbus

American experimental meteorology program operated by the NOAA

Those satellites have given atmosphere temperature at different altitudes


Program: Nimbus

Nimbus 1

Nimbus 2

Nimbus 3A

Nimbus 3

Nimbus 4

Nimbus 5

Nimbus 6

Nimbus 7


 Nimbus 1

General

Designation	00872 / 64052A
Launch date	28 Aug 1964
Country of origin	United States
Mission	Meteorology
Perigee/Apogee	429/937 km
Inclination	98.7°
Period	98.4 min
Launch vehicle	Thor Agena B
Launch site	Vandenberg
Mass at launch	376 kg

A circular orbit was intended but a partial failure of Agena (early shutdown) caused an elliptical orbit instead.

The project objectives were to provide improved photographs of local cloud conditions by an automatic picture transmission (APT) system, and to evaluate an advanced vidicon camera system for daylight coverage and a high-resolution infrared radiometer system for night-time cloud cover observation.

First high resolution photos (27000 photos taken) Five hurricanes and two typhoons were spotted in photographing 70 percent of the world each day. The APT system supplied daytime photos to more than 60 low-cost ground stations. Radiometer photos were remarkably clear and covered a 12,500 square mile area.

End of life

Out of service	23 Sep 1964
Cause	solar panel drive failed
Decay	16 May 1974


 Nimbus 2

General

Designation	02173 / 66040A
Launch date	15 May 1966
Country of origin	United States
Mission	Meteorology
Perigee/Apogee	1090/1174 km
Inclination	100.6°
Period	108 min
Launch vehicle	Thor Agena B
Launch site	Vandenberg

The project objectives were to provide global weather photography on a 24-hour basis for meteorological research and operational use, and provide infrared data for study of earth's heat balance.

Four sensor systems weighing a total of 142 pounds were carried. The advanced vidicon camera system (AVCS) included three 1-inch cameras with 800-line resolution designed to photograph a 800,000 square mile area. A high resolution infrared radiometer provided time and was expected to yield a variety of geophysical and atmospheric data including cloud height information.


 Nimbus 3A

Also called Nimbus B

General

Designation	n/a
Launch date	18 May 1968
Country of origin	United States
Mission	Meteorology
Launch vehicle	Thor Agena D
Launch site	Vandenberg

Two minutes after launch, a booster malfunction forced a command destruct. The booster and spacecraft fell into the Pacific Ocean between Vandenberg Air Force Base and San Miguel Island off the coast of California.

The radioactive fuel for the two generators (plutonium 238) was contained in two high-strength alloy and graphite capsules, which had been designed and tested to withstand ocean impact and seawater corrosion in case of such an abort.

End of life

Out of service	18 May 1968
Cause	Launcher failure


 Nimbus 3

General

Designation	03890 / 69037A
Launch date	14 Apr 1969
Country of origin	United States
Mission	Meteorology
Perigee/Apogee	1069/1128 km
Inclination	100°
Period	107.2 min
Launch vehicle	Thor Agena D
Launch site	Vandenberg

Nimbus 3 was a replacement for Nimbus 3A. Nimbus 3 was the first United States satellite to make night and day global measurements from space of temperatures of the atmosphere, both over extended periods and, for the first time, at varying levels vertically. While meteorological objectives were primary, this mission also gathered vital oceanographic data for scientific purposes other than solely for weather forecasting. Another mission objective was to provide data for the first experiment of the U.S.A. portion of the Global Atmospheric Research Program (GARP), which was an international program of formulating and coordinating research for achieving long-range global weather forecasting.

Technical data

Specifications

Prime contractor
Platform
Mass at launch
Mass in orbit	635 kg
Dimension	3 x 3.35 m
Solar array
Stabilization	3 axis
DC power
Design lifetime

Has a SNAP engine


 Nimbus 4

General

Designation	04362 / 70025A
Launch date	8 Apr 1970
Country of origin	United States
Mission	Meteorology
Perigee/Apogee	1085/1097 km
Inclination	99.9°
Period	107.1 min
Launch vehicle	Thor Agena D
Launch site	Vandenberg

It made world-wide weather observations twice a day - once in daylight and once in darkness.

Technical data

Specifications

Prime contractor
Platform
Mass at launch
Mass in orbit	683 kg
Dimension	3 x 3.35 m
Solar array	two panels: 0.91 x 2.44m
Stabilization
DC power	200 W
Design lifetime


 Nimbus 5

Also called Nimbus E

General

Designation	06305 / 72097A
Launch date	11 Dec 1972
Country of origin	United States
Mission	Meteorology
Perigee/Apogee	1086/1098 km
Inclination	99.8°
Period	107.1 min
Launch vehicle	Thor Delta #93

It was also used for testing advanced systems collecting meteorological and geological data.

Technical data

Specifications

Prime contractor
Platform
Mass at launch
Mass in orbit	790 kg
Dimension	3 x 3.35 m
Solar array	two panels: 0.91 x 2.44m
Stabilization
DC power	200 W
Design lifetime


 Nimbus 6

Also called Nimbus F

General

Designation	07924 / 75052A
Launch date	12 Jun 1975
Country of origin	United States
Mission	Meteorology
Perigee/Apogee	1098/1111 km
Inclination	99.8°
Period	107.4 min
Launch vehicle	Thor Delta #111
Mass at launch	829 kg or 911 kg?

Measures sea color


 Nimbus 7

Also called Nimbus G

General

Designation	11080 / 78098A
Launch date	24 Oct 1978
Country of origin	United States
Mission	Meteorology
Perigee/Apogee	944/956 km
Inclination	99°
Period	104 min
Orbital cycle	6 days
Launch vehicle	Thor Delta #145
Mass at launch	827 kg

Nimbus 7 was notable for providing the first daily mapping ozone concentration and the first global ocean color measurements. Data was for the first time used by ESA

Spacecraft and experiment data were transmitted to Earth stations immediately, or stored in an on-board high-speed tape recorder for subsequent playback when the satellite was in view of a ground acquisition station.

Technical data

Specifications

Prime contractor	GE Astro
Stabilization	3 axis

Equipped with numerous instruments: CZCS (Coastal Zone Color Scanner) out of service on 18 Dec 1986; ERBE (Earth Radiation Budget Experiment); LIMS (Limb IR Monitor of the Stratosphere) out of service mid 1989; SAM 2 (Stratospheric Aerosol Measurement 2) still working in 1992; SAMS (Stratospheric and Mesospheric Sounder) out of service in June 1983; SBUV/TOMS (Solar Backscatter Ultra-Violet/Total Ozone Mapping Spectrometer) SBUV out of service in February 1987, TOMS still working in 1992; SMMR (Scanning Multichannel Microwave Radiometer) out of service on 6 Jul 1988 and last but not least THIR (Temperature Humidity IR Radiometer) out of service in March 1985


 Program: NOAA

National Oceanic and Atmospheric Administration

Series of American weather satellites which evolved from a long line of experimental and operational satellites beginning with Tiros 1.

Instruments

Instruments on all satellites

Other instruments are used occasionnaly:

SBUV (Solar Backscatter UV radiometer) [on NOAA 11 onwards]: ozone distribution

ERBE (Earth Radiation Budget Experiment) [on NOAA 09 & 10]: radiation gains and losses (scanning instruments and non-scanner)

SARSAT [on NOAA 08 onwards]

Argos for data collection on NOAA second generation: 06 onwards

The primary command and data acquisition (CDA) stations are located in Fairbanks, Alaska, and Wallops Island, Va.


Program: NOAA

NOAA 01

NOAA 02

NOAA 03

NOAA 04

NOAA 05

NOAA 06

NOAA B

NOAA 07

NOAA 08

NOAA 09

NOAA 10

NOAA 11

NOAA 12

NOAA 13

NOAA 14

NOAA K


NOAA's specifications (2nd generation: Tiros N)

Prime contractor	GE Astro
Platform	based on the Tiros N bus
Mass at launch	1418 kg
Mass in orbit	735 kg
Dimension	3.71 m long x 1.88 m diameter
Solar array	2.37 x 4.91 m
Stabilization	3 axis
DC power
Design lifetime	3 years


NOAA's specifications (3rd generation)

Prime contractor	GE Astro
Platform	evolved from NOAA 2nd generation
Mass at launch	1420 kg
Mass in orbit	~1050 kg
Dimension	4.18 m long x 1.88 m diameter
Stabilization	3 axis
Design lifetime	3 years


NOAA's payload (NOAA 9 onwards)

AVHRR (Advanced Very High Resolution Radiometer)

Wavebands	0.58-0.68 µm (visible): cloud, snow and ice monitoring 0.725-1.10 µm (near IR): water, vegetation and agriculture surveys 3.55-3.93 µm (near IR): sea surface temperature, volcano, forest fire activity 10.3-11.3 µm (thermal IR): sea surface temperature, soil moisture 11.3-12.5 µm (thermal IR): sea surface temperature, soil moisture
Resolution	1.1 km
Swath width	3000 km
TOVS (Tiros Operational Vertical Sounder)

HIRS/2 (High Resolution IR Sounder): 20 channels in the 0.69 - 14 - 95 µm band; 17.4 km resolution

SSU (Stratospheric Sounding Unit): step-scanned far IR spectrometer with 3 channels in the CO² absorption band (15 µm);147.3 km resolution

MSU (Microwave Sounding Unit): passive 4-channel radiometer operating around 55 GHz; 109 km resolution


 NOAA 01

Also called Itos B

General

Designation	04793 / 70106A
Launch date	11 Dec 1970
Country of origin	United States
Mission	Meteorology
Perigee/Apogee	1421/1471 km
Inclination	101.3°
Period	114.8 min
Launch vehicle	Thor Delta #81
Mass at launch	306.8 kg

Images 24 hours a day


 NOAA 02

Also called Itos D

General

Designation	06235 / 72082A
Launch date	15 Oct 1972
Country of origin	United States
Mission	Meteorology
Perigee/Apogee	1446/1453 km
Inclination	102°
Period	114.9 min
Launch vehicle	Thor Delta #91
Mass at launch	340 kg


 NOAA 03

Also called Itos F

General

Designation	06920 / 73086A
Launch date	6 Nov 1973
Country of origin	United States
Mission	Meteorology
Perigee/Apogee	1499/1508 km
Inclination	102.2°
Period	116.1 min
Launch vehicle	Thor Delta #98
Mass at launch	340 kg


 NOAA 04

Also called Itos G

General

Designation	07529 / 74089A
Launch date	15 Nov 1974
Country of origin	United States
Mission	Meteorology
Perigee/Apogee	1442/1457 km
Inclination	102°
Period	114.9 min
Launch vehicle	Thor Delta #104
Mass at launch	340 kg


 NOAA 05

Also called Itos H

General

Designation	09057 / 76077A
Launch date	29 Jul 1976
Country of origin	United States
Mission	Meteorology
Perigee/Apogee	1504/1520 km
Inclination	102.2°
Period	116.3 min
Launch vehicle	Thor Delta #126


 NOAA 06

Also called NOAA A

General

Designation	11416 / 79057A
Launch date	27 Jun 1979
Country of origin	United States
Mission	Meteorology
Perigee/Apogee	785/800 km
Inclination	98.7°
Period	100.7 min
Launch vehicle	Atlas F
Launch site	Vandenberg

Based on Tiros N

End of life

Out of service	31 Mar 1987


 NOAA B

General

Designation	11819 / 80043A
Launch date	29 May 1980
Country of origin	United States
Mission	Meteorology
Perigee/Apogee	264/1445 km
Inclination	92.2°
Period	102.1 min
Launch vehicle	Atlas F
Launch site	Vandenberg
End of life

Out of service	29 May 1980
Cause	failed to reach a usable orbit
Decay	3 May 1981
Technical data

Specifications


 NOAA 07

Also called NOAA C

General

Designation	12553 / 81059A
Launch date	23 Jun 1981
Country of origin	United States
Mission	Meteorology
Perigee/Apogee	828/847 km
Inclination	98.9°
Period	101.7 min
Launch vehicle	Atlas F
Launch site	Vandenberg
Mass at launch	1405 kg
End of life

Out of service	Jun 1986
Cause	power system failure
Technical data

Specifications


 NOAA 08

Also called NOAA E

General

Designation	13923 / 83022A
Launch date	28 Mar 1983
Country of origin	United States
Mission	Meteorology
Perigee/Apogee	792/817 km
Inclination	98.6°
Period	101 min
Launch vehicle	Atlas F
Launch site	Vandenberg

Was a longer spacecraft than NOAA D (12) and was used to carry an additional Sarsat payload.

End of life

Out of service	29 Dec 1985
Cause	clock and power system failures
Technical data

Specifications

Prime contractor	GE Astro
Platform	based on the Tiros N bus, extended
Mass at launch	1418 kg?
Mass in orbit	735 kg?
Dimension	6.8 m long x 1.88 m diameter
Solar array	2.37 x 4.91 m?
Stabilization	3 axis
DC power
Design lifetime	3 years


 NOAA 09

Also called NOAA F

General

Designation	15427 / 84123A
Launch date	12 Dec 1984
Country of origin	United States
Mission	Meteorology
Perigee/Apogee	835/858 km
Inclination	99.158°
Period	101.8 min
Launch vehicle	Atlas E
Launch site	Vandenberg
Technical data

Specifications

Payload

APT downlink freq.	137.620 MHz (inoperative)
HRPT downlink freq.	1707.0 MHz
Beacon	137.770 MHz


 NOAA 10

Also called NOAA G

General

Designation	16969 / 86073A
Launch date	17 Sep 1986
Country of origin	United States
Mission	Meteorology
Perigee/Apogee	799/818 km
Inclination	98.549°
Period	101 min
Launch vehicle	Atlas E
Launch site	Vandenberg

The ERBE scanner had a scan sticking anomaly

End of life

Out of service	yes
Technical data

Specifications

Payload

APT downlink freq.	137.500 MHz (standby)
HRPT downlink freq.	1698.0 MHz
Beacon	136.770 MHz


 NOAA 11

Also called NOAA H

General

Designation	19531 / 88089A
Launch date	24 Sep 1988
Country of origin	United States
Mission	Meteorology
Perigee/Apogee	814/856 km
Inclination	99.059°
Period	101.9 min
Launch vehicle	Atlas E
Launch site	Vandenberg

Studies ozone

The attitude control subsystem lost two of its four gyros and was operated successfully with specialized onboard software.

End of life

Out of service	early 95
Cause	replaced by NOAA 14
Technical data

Specifications

Payload

APT downlink freq.	137.620 MHz (inoperative)
HRPT downlink freq.	1707.0 MHz
Beacon	137.770 MHz (inoperative?)


 NOAA 12

Also called NOAA D

General

Designation	21263 / 91032A
Launch date	14 May 1991
Country of origin	United States
Mission	Meteorology
Perigee/Apogee	804/824 km
Inclination	98.6°
Period	101.2 min
Equator crossing	19:30 northbound
Launch vehicle	Atlas E
Launch site	Vandenberg
End of life

Out of service	yes
Technical data

Specifications

Payload

APT downlink freq.	137.500 MHz (standby)
HRPT downlink freq.	1698.0 MHz
Beacon	136.770 MHz


 NOAA 13

Also called NOAA I

General

Designation	22739 / 93050A
Launch date	9 Aug 1993
Country of origin	United States
Mission	Meteorology
Perigee/Apogee	846/860 km
Inclination	98.9°
Period	102 min
Launch vehicle	Atlas E

Cost: $100 million

End of life

Out of service	Aug 1993
Cause	Failure (a screw damaged the power supply)
Technical data

Specifications

Payload


 NOAA 14

Also called NOAA J

General

Designation	23455 / 94089A
Launch date	30 Dec 1994 at 10:02 UT
Country of origin	United States
Mission	Meteorology
Perigee/Apogee	847/861 km
Inclination	98.9°
Period	102 min
Launch vehicle	Atlas E
Launch site	Vandenberg SLC3

It will replace NOAA 11 whose cloud cover imaging instrument had failed a few months ago. Besides an imaging radiometer, it carries optical sounders to monitor temperature and moisture content in the atmosphere, and counters to measure energetic electrons and protons.

A gas leak caused some difficulties in attitude control shortly after launch, but this has been resolved. The motor for the Microwave Sounding Unit on the NOAA-14 spacecraft has stopped working. Records show the unit is from a delivery made to Martin Marietta dating back to 1984! The microwave sounder returned to normal operation in May 1995 after a software patch was installed to cope with any repeat failure. Its life expectancy remains uncertain.

NOAA 14 also has a power-supply problem in its Sarsat receiver.

Technical data

Specifications

Payload

APT downlink freq.	137.500 MHz (standby)
HRPT downlink freq.	1698.0 MHz
Beacon	136.770 MHz


 NOAA K

General

Designation
Launch date	planned in Dec 1995
Country of origin	United States
Mission	Meteorology
Perigee/Apogee
Inclination
Period
Launch vehicle	Titan 2
Launch site	Vandenberg


NOAA

NOAA L, M, N and N prime are still to come, built by Martin Marietta. N and N' will be launched after the end of the contury


 Program: NOSS

Naval Ocean Surveillance System

American military ocean reconnaissance system

The first experimental satellite of this program could be 05678 / 71110A

Whitecloud (1976-1987, 9 satellites)

The NOSS constellation consists of three orbital planes, each containing four satellites flying in formation; a main satellite and three sub-satellites. Some believe that the satellites periodically deploy solar sails to provide the propulsion required to maintain their precise formation flight.

Another theory says the satellites would be connected by long (several km!) wires?

Some of the NOSS launches carried a LIPS (Living Plume Shield) subsatellite. In those cases a jetisonable toroidal plume shield, which protected the satellite from the exhaust of the Star-37E motor, was fittet with some solar-cell experiments.

The use of the Star-37E motor for the NOSS launches is somewhat conjectural, but is performance fits good with the published wights of the NOSS satellites.

Triplet (1990-..., 3 satellites)

Satellites equipped with infrared sensors, built by Martin Marietta, 3600 kg

The cluster could be composed of only the 3 sub-satellites?


Program: NOSS

NOSS 01

NOSS 02

NOSS 03

NOSS 04

NOSS 05

NOSS 06

NOSS 07

NOSS 08

NOSS 09

NOSS 12

NOSS 13

NOSS 14


 NOSS 01

Also called OPS 6431

General

Designation	08818 / 76038A
Launch date	30 Apr 1976
Country of origin	United States
Mission	Military: ocean reconnaissance (Whitecloud)
Perigee/Apogee	1128/1092 km
Inclination	63.5°
Period	107.5 min
Launch vehicle	Atlas F
Launch site	Vandenberg
Sub satellites

SSU 1 (08835 / 76038C)

SSU 2 (08836 / 76038D)

SSU 3 (08884 / 76038J)


 NOSS 02

Also called OPS 8781

General

Designation	10502 / 77112A
Launch date	8 Dec 1977
Country of origin	United States
Mission	Military: ocean reconnaissance (Whitecloud)
Perigee/Apogee	1054 / 1169 km
Inclination	63.4°
Period	107.5 min
Launch vehicle	Atlas F
Launch site	Vandenberg
Sub satellites

SSU 4 (10529 / 77112D)

SSU 5 (10544 / 77112E)

SSU 6 (10594 / 77112F)


 NOSS 03

Also called OPS 7245

General

Designation	11720 / 80019A
Launch date	3 Mar 1980
Country of origin	United States
Mission	Military: ocean reconnaissance (Whitecloud)
Perigee/Apogee	1035/1150 km
Inclination	63.0°
Period	107.1 min
Launch vehicle	Atlas F
Launch site	Vandenberg
Sub satellites

EP 1 (11731 / 80019C)

EP 2 (11732 / 80019D)

EP 3 (11745 / 80019G)


 NOSS 04

General

Launch date	9 Dec 1980
Country of origin	United States
Mission	Military: ocean reconnaissance (Whitecloud)
Launch vehicle	Atlas F
Launch site	Vandenberg
End of life

Out of service	9 Dec 1980
Cause	Launch failure


 NOSS 05

Also called OPS 0252

General

Designation	13791 / 83008A
Launch date	9 Feb 1983
Country of origin	United States
Mission	Military: ocean reconnaissance (Whitecloud)
Perigee/Apogee	1063/1186 km
Inclination	63.4°
Period	107.8 min
Launch vehicle	Atlas F
Launch site	Vandenberg
Sub satellites

SSA (13844 / 83008E)

SSB (13845 / 83008F)

SSC (13874 / 83008H)


 NOSS 06

Also called OPS 6432

General

Designation	14112 / 83056A
Launch date	9 Jun 1983
Country of origin	United States
Mission	Military: ocean reconnaissance (Whitecloud)
Perigee/Apogee	1051 / 1170 km
Inclination	63°
Period
Launch vehicle	Atlas F
Launch site	Vandenberg
Sub satellites

GB 1 (14143 / 83056C)

GB 2 (14144 / 83056D)

GB 3 (14180 / 83056G)


 NOSS 07

Also called OPS 8737

General

Designation	14690 / 84012A
Launch date	5 Feb 1984
Country of origin	United States
Mission	Military: ocean reconnaissance (Whitecloud)
Perigee/Apogee	1052 / 1168 km
Inclination	63.4°
Period
Launch vehicle	Atlas F
Launch site	Vandenberg
Sub satellites

JD 1 (14728 / 84012C)

JD 2 (14729 / 84012D)

JD 3 (14795 / 84012F)


 NOSS 08

Also called USA 015

General

Designation	16591 / 86014A
Launch date	9 Feb 1986
Country of origin	United States
Mission	Military: ocean reconnaissance (Whitecloud)
Perigee/Apogee	1049/1166 km
Inclination	63°
Period
Launch vehicle	Atlas F
Launch site	Vandenberg
Sub satellites

USA 016 (16624 / 86014E)

USA 017 (16625 / 86014F)

USA 018 (16631 / 86014H)


 NOSS 09

Also called USA 022

General

Designation	17997 / 87043A
Launch date	15 May 1987
Country of origin	United States
Mission	Military: ocean reconnaissance (Whitecloud)
Perigee/Apogee	1045/1179 km
Inclination	63°
Period
Launch vehicle	Atlas E/F
Launch site	Vandenberg
Sub satellites

USA 023 (18009 / 87043E)

USA 024 (18010 / 87043F)

USA 025 (18025 / 87043H)


 NOSS 12

Also called USA 059

General

Designation	20641 / 90050A
Launch date	8 Jun 1990
Country of origin	United States
Mission	Military: ocean reconnaissance (Triplet)
Perigee/Apogee	1200 km
Inclination	63°
Period
Launch vehicle	Titan 4

Could be in the same orbit as NOSS 09

Sub satellites

USA 060 (20682 / 90050B)

USA 061 (20691 / 90050C)

USA 062 (20692 / 90050D)


 NOSS 13

Also called USA 072

General

Designation	21775 / 91076A
Launch date	8 Nov 1991
Country of origin	United States
Mission	Military: ocean reconnaissance (Triplet)
Perigee/Apogee	1200 km
Inclination	63°
Period
Launch vehicle	Titan 4
Sub satellites

USA 074 (21799 / 91076C)

USA 076 (21808 / 91076D)

USA 077 (21809 / 91076E)


 NOSS 14

General

Launch date	2 Aug 1993
Country of origin	United States
Mission	Military: ocean reconnaissance (Triplet)
Launch vehicle	Titan 4
End of life

Out of service	2 Aug 1993
Cause	launcher explosion


 Program: Nova

American navigation program linked to Transit

Evolution compared to Transit satellites: transmitters (150 and 400 MHz) more powerful, on-board computer with larger memory (252 Kbits) that can save 5 days' data, better clock stability and capable of correcting its orbit.


Program: Nova

Nova 1

Nova 2

Nova 3


 Nova 1

Also called NNSS 30 480

General

Designation	12458 / 81044A
Launch date	15 May 1981
Country of origin	United States
Mission	Navigation
Perigee/Apogee	1164/1182 km
Inclination	90.1°
Period	108.9 min
Launch vehicle	Scout #102
Technical data

Transmits with 3 W on 150 MHz and 5 W on 400 MHz.


 Nova 2

Also called NNSS 30 500

General

Designation	15362 / 84110A
Launch date	12 Oct 1984
Country of origin	United States
Mission	Navigation
Perigee/Apogee	1149/1199 km
Inclination	89.9°
Period	108.9 min
Launch vehicle	Scout #104
Technical data

transmits with 3 W on 150 MHz and 5 W on 400 MHz


 Nova 3

Also called NNSS 30 490

General

Designation	19223 / 88052A
Launch date	16 Jun 1988
Country of origin	United States
Mission	Navigation
Perigee/Apogee	1150/1198 km
Inclination	90°
Period	108.9 min
Launch vehicle	Scout #111
Launch site	Vandenberg
Technical data

Transmits with 3 W on 150 MHz and 5 W on 400 MHz


 Program: NPOESS

National Polar-orbiting Operational Environmental Satellite System

Program to be launched in 2006. Is the follow on of DMSP and NOAA. This unique program is designed to save $300 million. it will consist of 3 satellites


 Program: OAO

Orbiting Astronomical Observatory

American astronomy mission


Program: OAO

OAO 1

OAO 2

OAO B

OAO 3


 OAO 1

General

Designation	02142 / 66031A
Launch date	8 Apr 1966
Country of origin	United States
Mission	Scientific: UV astronomy
Perigee/Apogee	782/793 km
Inclination	35°
Period	100.6 min
Launch vehicle	Atlas Agena D
Launch site	Cape Canaveral
End of life

Out of service	8 Apr 1966
Cause	Power failure


 OAO 2

General

Designation	03597 / 68110A
Launch date	7 Dec 1968
Country of origin	United States
Mission	Scientific: UV astronomy
Perigee/Apogee	751/757 km
Inclination	35°
Period	99.9 min
Launch vehicle	Atlas Centaur
Launch site	Cape Canaveral


 OAO B

End of life

Out of service	30 Nov 1970
Cause	Launch failure (Atlas Centaur)


 OAO 3

Also called Copernicus for the 500th anniversary of Copernic

General

Designation	06153 / 72065A
Launch date	21 Aug 1972
Country of origin	United States
Mission	Scientific: UV astronomy
Perigee/Apogee	714/723 km
Inclination	35°
Period	99.2 min
Launch vehicle	Atlas Centaur
Launch site	Cape Canaveral
Mass at launch	2200 kg
End of life

Out of service	18 Jan 1973


 Program: Ocean

Russian remote sensing program devoted to oceanographic applications.

Mission: all-weather ice and sea monitoring, including ice floe/ice pack movements. Flood and pollution monitoring.


Program: Ocean

Ocean-E

Cosmos 1076	Cosmos 1151
Ocean-OE

Cosmos 1500	Cosmos 1602
Ocean-O1

Cosmos 1766	Cosmos 1869	Ocean 1	Ocean 2	Ocean 3
Ocean 4


Ocean-O1's specifications

Platform	built by NPO Yuzhnoe
Mass at launch	1400 kg
Diameter	1.4 m
Height	3 m
Radar antenna	12 m
Stabilization	3 axis


Ocean-O1's payload

Side-looking Radar

Frequency	9.5 GHz (X-band)
Resolution	1.5 km
Swath width	460 km
MSU-M (Multispectral Scanner)

Wavebands	0.5-0.6; 0.6-0.7; 0.7-0.8; 0.8-1.1 µm
Resolution	1.5 km
Swath width	2000 km
MSU-S (Scanning Radiometer)

Wavebands	0.5-0.6; 0.6-0.7; 0.7-0.8; 0.8-1.1 µm
Resolution	200 m
Swath width	600 km


 Ocean 1

General

Designation	19274 / 88056A
Launch date	5 Jul 1988
Country of origin	CIS
Mission	Remote sensing
Perigee/Apogee	606/633 km
Inclination	82.5°
Period	97.1 min
Launch vehicle	Cyclone
Launch site	Plesetsk
Technical data

Specifications

Payload


 Ocean 2

General

Designation	20510 / 90018A
Launch date	28 Feb 1990
Country of origin	CIS
Mission	Remote sensing
Perigee/Apogee	618/645 km
Inclination	82.5°
Period	97.3 min
Launch vehicle	Cyclone
Launch site	Plesetsk
Technical data

Specifications

Payload


 Ocean 3

General

Designation	21397 / 91039A
Launch date	4 Jun 1991
Country of origin	CIS
Mission	Remote sensing
Perigee/Apogee	620/655 km
Inclination	82.5°
Period	97.5 min
Launch vehicle
Launch site	Plesetsk
Technical data

Specifications

Payload

Downlink frequency: 137.4 MHz


 Ocean 4

General

Designation	23317 / 94066A
Launch date	11 Oct 1994 at 13:30 UT
Country of origin	CIS (Russian/Ukrainian)
Mission	Remote sensing
Perigee/Apogee	631/665 km
Inclination	88.5°
Period	97.7 min
Launch vehicle	Cyclone + S5M
Launch site	Plesetsk LC32
Mass at launch	1950 kg
Technical data

Specifications

Payload

Built by NPO Yuzhnoe


Oderacs
 Program: Oderacs

Orbital DEbris RAdar Calibration System

US military spacecrafts intended to provide radar cross-sections of very small objects.


Program: Oderacs

Oderacs 1A	Oderacs 1B	Oderacs 1C	Oderacs 1D
Oderacs 1E	Oderacs 1F
Oderacs 2A	Oderacs 2B	Oderacs 2C	Oderacs 2D
Oderacs 2E	Oderacs 2F


 Oderacs 1A

General

Designation	22990 / 94006B
Launch date	3 Feb 1994
Country of origin	USA
Mission	Military: radar calibration
Perigee/Apogee	358/386 km
Inclination	59.9°
Period	91.7 min
Launch vehicle	STS 60

10 cm rough Aluminum sphere

End of life

Decay	2 Oct 1994


 Oderacs 1B

General

Designation	22991 / 94006C
Launch date	3 Feb 1994
Country of origin	USA
Mission	Military: radar calibration
Perigee/Apogee	358/386 km
Inclination	59.9°
Period	91.7 min
Launch vehicle	STS 60

10 cm polished Aluminum sphere

End of life

Decay	4 Oct 1994


 Oderacs 1C

General

Designation	22992 / 94006D
Launch date	3 Feb 1994
Country of origin	USA
Mission	Military: radar calibration
Perigee/Apogee	358/386 km
Inclination	59.9°
Period	91.7 min
Launch vehicle	STS 60

5 cm Aluminum sphere

End of life

Decay	?


 Oderacs 1D

General

Designation	22993 / 94006E
Launch date	3 Feb 1994
Country of origin	USA
Mission	Military: radar calibration
Perigee/Apogee	358/386 km
Inclination	59.9°
Period	91.7 min
Launch vehicle	STS 60

5 cm Aluminum sphere

End of life

Decay	?


 Oderacs 1E

General

Designation	22994 / 94006F
Launch date	3 Feb 1994
Country of origin	USA
Mission	Military: radar calibration
Perigee/Apogee	223/226 km
Inclination	57°
Period	89 min
Launch vehicle	STS 60

15 cm Aluminum sphere

End of life

Decay	3 Mar 1995


 Oderacs 1F

General

Designation	22995 / 94006G
Launch date	3 Feb 1994
Country of origin	USA
Mission	Military: radar calibration
Perigee/Apogee	198/202 km
Inclination	57°
Period	88.5 min
Launch vehicle	STS 60

15 cm Aluminum sphere

End of life

Decay	24 Feb 1995


 Oderacs 2A

General

Designation	23471 / 95004C
Launch date	4 Feb 1995 at 04:57 UT
Country of origin	USA
Mission	Military: radar calibration
Perigee/Apogee	314/336 km
Inclination	51.6°
Period	91 min
Launch vehicle	STS 63

10.16 cm diameter Al sphere


 Oderacs 2B

General

Designation	23472 / 95004D
Launch date	4 Feb 1995 at 04:57 UT
Country of origin	USA
Mission	Military: radar calibration
Perigee/Apogee	314/336 km
Inclination	51.6°
Period	91 min
Launch vehicle	STS 63

15.24 cm dia. Al sphere

End of life

Decay	29 Sep 1995


 Oderacs 2C

General

Designation	23473 / 95004E
Launch date	4 Feb 1995 at 04:57 UT
Country of origin	USA
Mission	Military: radar calibration
Perigee/Apogee	314/336 km
Inclination	51.6°
Period	91 min
Launch vehicle	STS 63

5.08 cm diameter steel sphere


 Oderacs 2D

General

Designation	23474 / 95004F
Launch date	4 Feb 1995 at 04:57 UT
Country of origin	USA
Mission	Military: radar calibration
Perigee/Apogee	314/336 km
Inclination	51.6°
Period	91 min
Launch vehicle	STS 63

13.208 cm long dipole wire

End of life

Decay	2 Mar 1995


 Oderacs 2E

General

Designation	23475 / 95004G
Launch date	4 Feb 1995 at 04:57 UT
Country of origin	USA
Mission	Military: radar calibration
Perigee/Apogee	314/336 km
Inclination	51.6°
Period	91 min
Launch vehicle	STS 63

13.208 cm long dipole wire

End of life

Decay	27 Feb 1995


 Oderacs 2F

General

Designation	23476 / 95004H
Launch date	4 Feb 1995 at 04:57 UT
Country of origin	USA
Mission	Military: radar calibration
Perigee/Apogee	314/336 km
Inclination	51.6°
Period	91 min
Launch vehicle	STS 63

4.318 cm length dipole wire


 Program: Odyssey

TRW (US-based) and Canada's Teleglobe announce intent to form Odyssey Worldwide Services to operate and market TRW's medium-orbit Odyssey cellular-comsat system. Odyssey first launch is set for 1998, FCC licensing permitting. Satellites are to be launched two at a time by Atlas 2AS class launchers. Connections will go via one satellite to one of 10-11 ground stations, where they will be routed into the normal phone system; there will be no intersatellite links.

LM could be used to launch some of the 12 birds

The project is worth $3 billion. TRW Inc. could seek to raise as much as $900 million in the junk bond market in late 1997 or 1998

Overview

Orbit type	MEO
Orbit range	10354 km
Nb of satellites	12 + 3 backup
Nb of planes	3
Inclination	55°
Nb beams per satellite	37
Coverage	10540 km²
Modulation	CDMA
Mobile uplink freq.	S-Band: 2483.5 - 2500 MHz
Satellite mass	1950 kg
Coverage	Worldwide
Operational date	2000 (planned)
Specifications

Prime contractor	Matra Marconi?
Platform
Mass at launch
Mass in orbit
Dimension
Solar array
Stabilization
DC power
Design lifetime	10 years
Payload

Capacity	2300 phone circuits
Voice	4800 bps
Fax	yes
Data	9600 bps
Mobile Downlink freq.	1610 - 1621.35 MHz


 Program: Offek

First Israeli program


Program: Offek

Offek 1

Offek 2

Offek 3


 Offek 1

Means "Horizon 1"

General

Designation	19519 / 88087A
Launch date	19 Sep 1988
Country of origin	Israel
Mission	Technology
Perigee/Apogee	250/1149 km
Inclination	142.9° (retrograd orbit)
Period	98.8 min
Launch vehicle	Shavit
Launch site	Palmahim
Mass at launch	156 kg

First Israeli satellite

End of life

Decay	14 Jan 1989


 Offek 2

Means "Horizon 2"

General

Designation	20540 / 90027A
Launch date	3 Apr 1990
Country of origin	Israel
Mission	Technology
Perigee/Apogee	149/251 km
Inclination	143.2° (retrograd orbit)
Period	88.5 min
Launch vehicle	Shavit
Launch site	Palmahim
End of life

Decay	9 Jul 1990


 Offek 3

Means "Horizon 3"

General

Designation	23549 / 95018A
Launch date	5 Apr 1995 at 11:16 UT
Country of origin	Israel
Mission	Technology
Perigee/Apogee	369/729 km
Inclination	143.4° (retrograd orbit)
Period	95.6 min
Launch vehicle	Shavit
Launch site	Palmahim
Mass at launch	225 kg

Reported by Israel's media as the first spy satellite... but it's most likely not a fullyfleged spy satellite.

Offek 3 is the first of the second-generation light satellites for Israel. With its three-axis stabilization, the system is being proposed and marketed by Israel Aircraft Industries and MLM System Engineering and Integration to carry payloads for astronomy and remote sensing purposes. The light-weight electro-optical scanner or Earth Resources Monitoring System carried aboard this mission was developed by El-Op. Equipped with a high-resolution camera.


 OFO

General

Designation	04690 / 70094A
Launch date	9 Nov 1970
Country of origin	United States
Mission	Scientific
Perigee/Apogee	304/518 km
Inclination	37.4°
Period	92.6 min
Launch vehicle	Scout #70
End of life

Decay	9 May 1971


 Program: OGO

Orbiting Geophysical Observatory

American scientific program of standardized spacecraft capable of conducting many related experiments.


Program: OGO

OGO 1

OGO 2

OGO 3

OGO 4

OGO 5

OGO 6


 OGO 1

General

Designation	00879 / 64054A
Launch date	5 Sep 1964
Country of origin	United States
Mission	Scientific: magnetosphere study
Perigee/Apogee	4930/144824 km
Inclination	40.7°
Period	3841.9 min
Launch vehicle	Atlas Agena B
Launch site	Cape Canaveral

OGO I carried 20 experiments, more than any previous satellite. The spacecraft's highly elliptical orbit was planned to permit correlated investigations of geophysical and solar phenomena in the Earth's atmosphere and magnetosphere, and in interplanetary space.

Two experiment booms failed to deploy properly, however, and one of these booms obscured the horizon scanner's view of Earth. As a result, spacecraft attitude could not be Earth oriented and OGO I remained spin stabilized at 5 rpm. The solar panels were turned to a more favorable sun angle and all 20 experiments were able to provide data.

OGO 1, together with data from Explorer 21, has indicated the source of much of the Van Allen belt's high-energy radiation as the solar wind - entering the magnetosphere through weak field lines in the magnetosphere's tail on the side of the Earth opposite the sun.

Technical data

Specifications

Prime contractor
Platform
Mass at launch	523 kg
Payload mass	95 kg
Dimension	18 x 6 m
Solar array	32000 solar cells + nickel-cadmium batteries
Stabilization	spin stabilized
DC power
Design lifetime

Spacecraft systems included a communication and data handling system to store up to 128,000 bits per second.


 OGO 2

General

Designation	01620 / 65081A
Launch date	14 Oct 1965
Country of origin	United States
Mission	Scientific: magnetosphere study
Perigee/Apogee	419/1515 km
Inclination	87.4°
Period	104.4 min
Launch vehicle	Thor Agena
Launch site	Vandenberg
End of life

Decay	17 Sep 1981


 OGO 3

General

Designation	02195 / 66049A
Launch date	7 Jun 1966
Country of origin	United States
Mission	Scientific: magnetosphere study
Perigee/Apogee	19519/102806 km
Inclination	77.6°
Period	2911.5 min
Launch vehicle	Atlas Agena B
Launch site	Vandenberg?

The orbit of this satellite remains uncertain. Other sources give 319/122173 km x 31.39 deg x 2915 min. This seems unprobable since with such a low perigee the satellite would have reentred.


 OGO 4

General

Designation	02895 / 67073A
Launch date	28 Jul 1967
Country of origin	United States
Mission	Scientific: magnetosphere study
Perigee/Apogee	422/885 km
Inclination	86°
Period	97.8 min
Launch vehicle	Thor Agena D
Launch site	Vandenberg
End of life

Decay	16 Aug 1972


 OGO 5

General

Designation	03138 / 68014A
Launch date	4 Mar 1968
Country of origin	United States
Mission	Scientific: magnetosphere study
Perigee/Apogee	271/148186 km
Inclination	54°
Period	3795.9 min
Launch vehicle	Atlas Agena D
Launch site	Cape Canaveral


 OGO 6

General

Designation	03986 / 69051A
Launch date	5 Jun 1969
Country of origin	United States
Mission	Scientific: magnetosphere study
Perigee/Apogee	397/1089 km
Inclination	82°
Period	99.7 min
Launch vehicle	Atlas Agena D
Launch site	Vandenberg
End of life

Decay	12 Oct 1979


 Ohsumi

Named as its launch site

General

Designation	04330 / 70011A
Launch date	11 Feb 1970
Country of origin	Japan
Mission
Perigee/Apogee	323/2.416 km
Inclination	31°
Period	113.1 min
Launch vehicle	Lambda L 4S
Launch site	Kagoshima
Mass at launch	23.8 kg

First Japanese satellite


 Olympus

Also called L SAT (Large SATellite)

General

Designation	20122 / 89053A
Launch date	12 Jul 1989
Country of origin	Europe
Mission	Telecommunications
Geostationary orbit	19°W
Launch vehicle	Ariane V32
End of life

Out of service	12 Aug 1993
Cause	Out of control

The control's satellite was lost on 29 May 1991 because of a stabilization problem that caused an electric interruption. The satellite then drifted over Pacific and Atlantic. It was found by radars and the control was taken over by the ESA's station in Darmstadt on 19 Jun 1992. It was then put back into service on 7 Aug 1992.

On 12 Aug 1993 it started rotating and fell in backup mode to try to stabilize (during the Perseid shower). It consumed so much ergols that there was not enough left to bring it back in service. The spacecraft was send to the junk orbit.

Technical data

Specifications

Prime contractor	British Aerospace (now MMS)
Platform	Olympus
Mass at launch	2595 kg
Payload mass	359 kg
Dimension	2.9 x 2.7 x 5.6 m
Solar array	26 m span
DC power	EOL: 3600 W
Stabilization	3 axis
Design lifetime	7 years
Ku-band

Main transponders	2 (DBS) + 4
Backup transponders
Power	DBS: 2 transponders of 230 W (TWTA) others: 4 transponders of 30 W (TWTA)
Bandwidth	DBS: 27 MHz others: 18 & 36 MHz
Coverage	DBS: Italy and Europe (steerable) others: 5 spots
EIRP	DBS: 63 dBW others: 33.3 dBW
Polarization
Frequencies	DBS: 12/18 GHz others: 12/14 GHz
Ka-band (20/30 GHz)

Main transponders	2
Backup transponders	1
Power	30 W (TWTA)
Bandwidth	40 & 700 MHz
Coverage	2 steerable spot beams
EIRP	52.1 dBW
Polarization

Equipped with 5 steerable antennas for numerous experiments (direct TV and HDTV). Also equipped with 3 beacons at 12, 20 and 30 GHz for propagation measurements. Non Ku-band DBS transponders are designed for digital transmissions in AMRT with an on-board matrix commuter.


 Program: Optus

Australian telecommunication satellite system operated by Optus communications. Formerly knowned as Aussat.

Contact

Optus Communications

101 Miller Street, North Sydney, NSW 2060, Australia

Tel: +61-2-342-7800

Fax: +61-2-342-7100


Program: Optus

Optus A1	Optus A2	Optus A3
Optus B1	Optus B2	Optus B3


Optus A's specifications

Prime contractor	Hughes
Platform	HS-376
Mass at launch	1250 kg
Dry mass	540 kg
Mass in orbit	655 kg
Diameter	2.16 m
Height	6.6 m (2.84 m stowed)
Stabilization	Spin stabilized
DC power	1000 W
Design lifetime	7 years (10 for the A3)
Video carrier

Receiver bandwidth	30 MHz
Peak to peak deviation	22.3 MHz/V


Optus A's Ku-band

Main transponders	11+4
Backup transponders	2+2
Power	(11+2) transponders of 12 W (TWTA) (4+2) transponders of 30 W (TWTA)
Bandwidth	45 MHz
Coverage	Australia, New Zealand and New Guinea
EIRP	12 W: 41 dBW 30 W: 51 dBW
Polarization


Optus A's antenna specifications

Beam	Transponders
National A	1, 3, 4, 6 and 7
South Eastern Australia	1, 3, 5, 7 and 8
Western Australia	2, 4, 7 and 8
Papua New Guinea or South West pacific	4, 6 and 7
National B	9, 10, 12, 13, 14 and 15
North Eastern	9, 11, 14 and 15
Central Australia	10, 12, 14 and 15

This chart gives the possible transponders with beams connections. Alternative selection of Papua New Guinea or South West pacific beams is possible with Optus A3.


Optus A's transponder frequency chart (GHz)

Horizontal uplink	Horizontal downlink	Transponder	Vertical downlink	Vertical uplink
14.025		1	12.277
14.089		2	12.341
14.153		3	12.405
14.217		4	12.469
14.281		5	12.553
14.345		6	12.597
14.409		7 (30 W)	12.661
14.473		8 (30 W)	12.725
	12.309	9		14.057
	12.373	10		14.121
	12.437	11		14.185
	12.501	12		14.249
	12.565	13		14.313
	12.629	14 (30 W)		14.377
	12.693	15 (30 W)		14.441


Optus B's specifications

Prime contractor	Hughes
Platform	HS-601
Mass at launch	2858 kg
Dry mass	1270 kg
Mass in orbit	1582 kg
Dimension	2.27 x 2.27 x 2.27 m
Solar array	20 m span
Stabilization	3 axis
DC power	BOL: 3500 W EOL: 3000 W
Design lifetime	13.7 years

Carries a Ka-band beacon (30 GHz) and a laser retroreflector for precise satellite location and time transfer demonstrations.

Video carrier

Receiver bandwidth	25 MHz
Peak to peak deviation	17.74 MHz/V


Optus B's L-band

Main transponders	2 (inbound and outband)
Power	150 W (8 SSPA)
Total bandwidth	14 MHz
Coverage	Australia
EIRP	49 dBW
Polarization	RHCP


Optus B's Ku-band

Main transponders	15+1 (L-band downlink)
Backup transponders	6
Power	50 W (TWTA)
Bandwidth	54 MHz
Coverage	Australia (1 national beam and 5 regional beams) High Performance beam
EIRP	47 dBW
Polarization	linear


Optus B's antenna specifications

Beam	Transponders
National A	1, 2, 3, 4, 5, 6, 7 and 8
New Zealand	1, 2, 3, 4, 5, 6, 7 and 8
South Eastern Australia	1, 2, 3, 4, 5, 6, 7 and 8
Western Australia	6, 7 and 8
National B	9, 10, 11, 12, 13, 14 and 15
High performance	9, 10, 11, 12, 13, 14 and 15
North Eastern	11, 14 and 15
Central Australia	12, 14 and 15

This chart gives the possible transponders with beams connections. The National A, South Eastern Australia and Western Australia beams can be combined with the New Zealand beam: the power split is 20% to New Zealand and 80% for the other beam.


Optus B's transponder frequency chart (GHz)

Horizontal uplink	Horizontal downlink	Transponder	Vertical downlink	Vertical uplink
14.0299		1	12.2819
14.0925		2	12.3445
14.1551		3	12.4071
14.2177		4	12.4697
14.2803		5	12.5323
14.3429		6	12.5949
14.4055		7	12.6575
14.4681		8	12.7201
	12.3132	9		14.0612
	12.3758	10		14.1238
	12.4384	11		14.1864
	12.5010	12		14.2490
	12.5636	13		14.3116
	12.6262	14		14.3742
	12.6888	15		14.4368
Mobile communication (L-band to Ku-band & Ku-band to L-band):

	12.2705	M (16)		1.6535 (RHCP)
	1.5520 (RHCP)	M (16)		14.0185


Optus B's EIRP (National beam)


Optus B's EIRP (Australian spot beams)


Optus B's EIRP (High Performance beam)


 Optus A1

Also called Aussat A1

General

Designation	15993 / 85076B
Launch date	27 Aug 1985
Country of origin	Australia
Mission	Telecommunications
Geostationary orbit	life time in 160°E
Launch vehicle	STS 27
End of life

Out of service	yes
Technical data

Specifications

Antenna specifications

Ku-band

Transponder frequency chart


 Optus A2

Also called Aussat A2

General

Designation	16275 / 85109C
Launch date	27 Nov 1985
Country of origin	Australia
Mission	Telecommunications
Geostationary orbit	see below
Launch vehicle	STS 31
Location

Begin	End	Position
L: 27 Nov 1985		156°E
Feb 1995		164°E, inclined
Technical data

Specifications

Antenna specifications

Ku-band

Transponder frequency chart


 Optus A3

Also called Aussat A3

General

Designation	18350 / 87078A
Launch date	16 Sep 1987
Country of origin	Australia
Mission	Telecommunications
Geostationary orbit	see below
Launch vehicle	Ariane V19
Location

Begin	End	Position
L: 16 Sep 1987		164°E
Feb 1995		156°E
Aug 1995		152°E, inclined
Technical data

Specifications

Antenna specifications

Ku-band

Transponder frequency chart

EIRP coverage (dBW)

Central beam

Australian spot beams


Optus A3's EIRP (National beam)

Add 4 to 5 dBW for 30 W transponders


Optus A3's EIRP (Australian spot beams)

Add 4 to 5 dBW for 30 W transponders


 Optus B1

General

Designation	22087 / 92054A
Launch date	13 Aug 1992
Country of origin	Australia
Mission	Telecommunications
Geostationary orbit	160°E
Launch vehicle	Long March 2E (First commercial flight)
Launch site	Xichang
Technical data

Specifications

Antenna specifications

L-band

Ku-band

Transponder frequency chart

EIRP coverage (dBW)

Central beam

Australian spot beams

High Performance beam


 Optus B2

General

Designation	22278 / 92090A
Launch date	21 Dec 1992 at 11:20 UT
Country of origin	Australia
Mission	Telecommunications
Geostationary orbit	n/a
Launch vehicle	Long March 2E
Launch site	Xichang
End of life

Out of service	21 Dec 1992
Cause	The satellite was destroyed when the fairing area of the launch vehicle was destroyed some 47 seconds after liftoff. The cause of the failure is still subject to some speculation and disagreement but was almost certainly due to wind shear effects encountered just after liftoff. The Optus B series of satellites have a liquid propulsion apogee engine (not solid propelled motor). They do, however, have a solid perigee stage when launched on Long March 2E. It is almost certain that this solid motor (plus a few remnants of the satellite itself) is all that was delivered into orbit.
Technical data

Specifications

Antenna specifications

L-band

Ku-band

Transponder frequency chart

EIRP coverage (dBW)

Central beam

Australian spot beams

High Performance beam


 Optus B3

This spacecraft is also called Optus B2R

General

Designation	23227 / 94055A
Launch date	27 Aug 1994 at 21:10 UT
Country of origin	Australia
Mission	Telecommunications
Geostationary orbit	see below
Launch vehicle	Long March 2E
Launch site	Xichang
Location

Begin	End	Position
L: 27 Aug 1994	Jul 1995	152°E
Aug 1995		156°E
Technical data

Specifications

Antenna specifications

L-band

Ku-band

Transponder frequency chart

EIRP coverage (dBW)

Central beam

Australian spot beams

High Performance beam


 Program: Orbcomm

Operated by Orbcomm whose parent companies are Orbital Sciences Corp. (Boulder, Colorado) and Teleglobe Inc.

Telecommunication program: network of LEO satellites to relay the GPS-determined locations of cargo trucks, and data from oil pipeline monitors.

Orbcomm has signed in Sep 1995 the final financing and contruction agreements for an expanded 36-Orbcomm satellite constellation, with Canada's Teleglobe investing $85 million and OSC $75 million. Each company will own 50% of the Orbcomm global operating company.

Full-time service will begin when 26 satellites are in orbit. The full network will be composed of 4 near-polar satellites and 32 satellites inclined at 45°. Altitude: about 775 km

Contact

ORBCOMM

21700 Atlantic Boulevard, Dulles, Virginia 20166-6801 USA

Tel: 1-800-orbcomm

Tel: +1-703-406-6000

Fax: +1-703-406-3504

Email: orbcomm@orbital.com

Technical data

Orbcomm FM

Uplink frequencies: 148.00-149.90 MHz

Downlink frequencies: 137.050, 135.225, 137.575 & 137.985 MHz and 400.05-400.15 MHz

Subscriber communicators transmit at 2400 bps and receive at 4800 bps

Addressing is done with the X400 protocol


Program: Orbcomm

Orbcomm X

Orbcomm XP 1

Orbcomm FM 1

Orbcomm FM 2


Orbcomm FM's specifications

Prime contractor	OSC
Platform	Microstar
Mass at launch	40 kg
Mass in orbit
Diameter	1.04 m stowed
Height	0.165 m stowed
Width	2.2235 m deployed
Stabilization	gravity gradient
DC power
Design lifetime
Telemetry	57.6 kbps in VHF

Deploys a 3.28 m long VHF/UHF communications antenna.


 Orbcomm X

General

Designation	21576 / 91050C
Launch date	17 Jul 1991
Country of origin	United States
Mission	Telecommunications
Perigee/Apogee	764/771 km
Inclination	98.4°
Period	100.2 min
Launch vehicle	Ariane V44
Mass at launch	22.8 kg

Experimental satellite. Should provide emergency services.


 Orbcomm XP 1

Also called OXP 1 or Orbcomm CDS (Capabilities Demonstration Satellite)

General

Designation	22489 / 93009A
Launch date	9 Feb 1993
Country of origin	United States
Mission	Telecommunications
Perigee/Apogee	727/790 km
Inclination	25°
Period	100 min
Launch vehicle	Pegasus #3
Launch site	Vandenberg

Experimental satellite


 Orbcomm FM 1

General

Designation	23545 / 95017A
Launch date	3 Apr 1995 at 13:48 UT
Country of origin	United States
Operator	Orbital Communications (OSC's subsidiary)
Mission	Telecommunications
Perigee/Apogee	727/756 km
Inclination	70°
Period
Launch vehicle	Pegasus #8
Launch site	Vandenberg

Had stopped sending signals short after launch but control was regained in mid May 1995.

Technical data

Specifications


 Orbcomm FM 2

General

Designation	23546 / 95017B
Launch date	3 Apr 1995 at 13:48 UT
Country of origin	United States
Operator	Orbital Communications (OSC's subsidiary)
Mission	Telecommunications
Perigee/Apogee	727/756 km
Inclination	70°
Period
Launch vehicle	Pegasus #8
Launch site	Vandenberg

The uplink antenna was malfunctionning after launch and the satellite didn't receive any signals from the ground station. After a month the problems appeared to be solved.

Technical data

Specifications


 Program: Orion

American telecommunication program operated by Orion Satellite Corporation

Orion Atlantic is a joint venture of eight multinational corporations: Martin Marietta, British Aerospace and Kingston Communications of England, COM DEV of Canada, Matra of France, Nissho Iwai of Japan, STET of Italy and Orion Network Systems of the United States.

Contact

Orion Network Systems Inc.

2440 Research Boulevard, Suite 400, Rockville, MD 20850, USA

Tel:	US: 1-800-78-ORION
Int: +1-301-258-8101
Fax:	+1-301-258-8119


Program: Orion

Orion 1

Orion 2

Orion 3

Orion 4


Orion 1's EIRP (Broad beam to Europe)


Orion 1's EIRP (Spot beams to Europe)


Orion 1's EIRP (Broad beam to US)


Orion 1's EIRP (Spot beams to US)


 Orion 1

General

Designation	23413 / 94079A
Launch date	29 Nov 1994
Country of origin	United States
Mission	Telecommunications
Geostationary orbit	37.5°W
Launch vehicle	Atlas Centaur

The Centaur delivered Orion 1 into an unprecedented elliptical transfer orbit of 403 x 122762 km x 25.5°. The orbit was then raised to 25010 km x 122766 km x 3.0°. The apogee was then lowered until reaching GEO. The fuel-saving high apogee transfer technique had been used before, but never with such an extreme apogee.

Technical data

EIRP coverage (dBW)

Broad beam to Europe

Spot beams to Europe

Broad beam to US

Spot beams to US

Specifications

Prime contractor	Matra Marconi Space
Platform	Eurostar 2000
Mass at launch	2350 kg
Payload mass	375 kg
Dimension	1.7 x 1.6 x 2.1 m
Stabilization	3 axis
DC power	EOL: 3200 W
Payload power	2500 W (in eclipse)
Design lifetime	12 years
Ku-band

Main transponders	34
Backup transponders
Power	15 W
Bandwidth	6 transponders of 36 MHz 28 transponders of 54 MHz
Coverage	3 spots and 1 zone beam to Europe 4 spots and 1 zone beam to America
EIRP	Spot beam: 50 dBW Zone beam: 45 dBW
Polarization	Linear
Transponder frequencies

Europe uplink	14.0 - 14.5 GHz
Europe downlink	11.45 - 11.7 GHz & 12.5 - 12.75 GHz
North Am. uplink	14.0 - 14.5 GHz
North Am. downlink	11.7 - 12.2 GHz
Transponder frequency chart to Europe (GHz)

Horizontal Downlink	Transponder	Vertical Downlink	Bandwidth	Beam
	5	11.483	54 MHz
11.483	14		54 MHz	NE/CE/SE
	6	11.546	54 MHz
11.546	15		54 MHz
	7	11.609	54 MHz
11.609	16		54 MHz
	8	11.672	54 MHz
11.672	17		54 MHz
	1	12.528	54 MHz
12.528	9		54 MHz	EBB
	2	12.591	54 MHz	EBB
12.591	10		54 MHz
12.645	11		36 MHz	NE & CE
	3	12.654	54 MHz	EBB
12.685	12		36 MHz	NE
	4	12.717	54 MHz
12.726	13		36 MHz

EBB = European Broad Beam, NE = North European, CE: Central European, SE: South European


 Orion 2

General

Designation
Launch date	planned in early 1998
Country of origin	United States
Mission	Telecommunications
Geostationary orbit	12°W
Launch vehicle	Atlas
Technical data

Specifications

Prime contractor	Matra Marconi Space
Platform	Eurostar
Mass at launch	3200 kg
Payload mass
Dimension
Stabilization	3 axis
DC power	7000 W
Design lifetime	13 years
Ku-band

Main transponders	32
Backup transponders
Power
Bandwidth
Coverage	Eastern United States South America Europe Former Soviet Union through to the Ural mountains Middle East Northern Africa
EIRP
Polarization

on-board switching & frequency re-use


 Orion 3

Construction is to begin in 1997

slot: 126°E: Asia Pacific region ranging from India to Hawaii


 Orion 4

For 1999 between 127°W and 135°W

total cost: $210 million

3-axis stabilized, 16 transponders in Ku-band


 Program: Oscar

Orbiting Satellite Carrying Amateur Radio

HAM radio satellite program. Oscar is a generical name for numerous satellites, they are often identified as #O-xx where # is the initial of an organization and xx the number of the satellite in the Oscar program.


Program: Oscar

Oscar 01	AO-10: Oscar 10	FO-20: Fuji 1B
Oscar 02	UO-11: Uosat 2	AO-21: Informator
Oscar 03	FO-12: Fuji 1A	UO-22: Uosat 5
Oscar 04	AO-13: Oscar 13	KO-23: Kitsat A
Oscar 05	UO-14: Uosat 3	#24 was reserved for Arsène
AO-06: Oscar 06	UO-15: Uosat 4	KO-25: Kitsat B
AO-07: Oscar 07	AO-16: Pacsat	IO-26: Itamsat
AO-08: Oscar 08	DO-17: Dove	AO-27: Eyesat
Oscar 09 failure	WO-18: Webersat	PO-28: Posat
UO-09: Uosat 1	LO-19: Lusat	Phase 3D


 Oscar 01

General

Designation	00214 / 61034B
Launch date	12 Dec 1961
Country of origin	United States
Mission	Telecommunications
Perigee/Apogee	245/474 km
Inclination	81.2°
Period	91.8 min
Launch vehicle	Thor Agena B
Launch site	Vandenberg
Mass at launch	4.5 kg
End of life

Decay	31 Jan 1962


 Oscar 02

General

Designation	00305 / 62022B
Launch date	2 Jun 1962
Country of origin	United States
Mission	Telecommunications
Perigee/Apogee	188/339 km
Inclination	74.2°
Period	89.8 min
Launch vehicle	Thor Agena B
Launch site	Vandenberg
End of life

Decay	21 Jun 1962


 Oscar 03

General

Designation	01293 / 65016F
Launch date	9 Mar 1965
Country of origin	United States
Mission	Telecommunications
Perigee/Apogee	874/902 km
Inclination	70.1°
Period	102.7 min
Launch vehicle	Thor Agena D
Launch site	Vandenberg

First Amateur satellite with solar power. First transponder. Transponder operational life 18 days (battery-limited). The 2 beacons operated for several months from the solar cells.

Technical data

Specifications

Mass at launch	18 kg
Stabilization	none
DC power	2.5 W: solar cells; battery

Transponder: 1W, 50kHz bandwidth, 146 MHz uplink, 144 MHz downlink (linear translator).


 Oscar 04

General

Designation	01902 / 65108C
Launch date	21 Dec 1965
Country of origin	United States
Mission	Telecommunications
Perigee/Apogee	162/33549 km
Inclination	26.8°
Period	587.5 min
Launch vehicle
Launch site	Cape Canaveral
End of life

Decay	12 Apr 1976

Built by TRW radio club. Intended on a high altitude but the launch vehicle had a partial failure

Technical data

Specifications

Stabilization	Spin generated by a spring on separation from launch vehicle
DC power	10 W, battery

Beacon: 432 MHz. No telemetry


 Oscar 05

Also called Australis

General

Designation	04321 / 70008B
Launch date	23 Jan 1970
Country of origin	Australia
Mission	Telecommunications
Perigee/Apogee	1431/1475 km
Inclination	101.4°
Period	115 min
Launch vehicle
Launch site	Vandenberg

Built at University of Melbourne, Australia. Launched with Tiros weather satellite. Command receiver (on 2m) and hardwired decoder (first remote control of an amateur satellite). Operational life: 46 days.

Technical data

Specifications

Stabilization	Passive magnetic


 Oscar 06

Also called AO-06 or Phase 2A

General

Designation	06236 / 72082B
Launch date	15 Oct 1972
Country of origin	United States
Mission	Telecommunications
Perigee/Apogee	1446/1452 km
Inclination	102°
Period	114.9 min
Launch vehicle
Launch site	Vandenberg

First complex control system (discrete logic). First satellite-satellite communication (via Oscar 07). Demonstrated Doppler-location of ground stations for search and rescue. Demonstrated low-cost medical data relay from remote locations.

End of life

Out of service	21 Jun 1977
Cause	Battery failure
Technical data

Specifications

Stabilization	Passive magnetic
DC power	5.5 W (NiCd battery)

1 W downlink, 435 MHz beacon


  Oscar 07

Also called AO-07

General

Designation	07530 / 74089B
Launch date	15 Nov 1974
Country of origin	United States
Mission	Telecommunications
Perigee/Apogee	1438/1456 km
Inclination	101.9°
Period	114.8 min
Launch vehicle	Thor Delta #104

Early demonstrations of low-budget medical data relay and doppler location of ground transmitters for search-and-rescue operations were done using this satellite.

End of life

Out of service	1980
Cause	Battery failure
Technical data

Specifications

Stabilization	Passive magnetic
DC power	15 W (NiCd battery)


 Oscar 08

Also called AO-08 or Phase 2D

General

Designation	10703 / 78026B
Launch date	5 Mar 1978
Country of origin	United States
Mission	Telecommunications
Perigee/Apogee	893/903 km
Inclination	99.2°
Period	103 min
Launch vehicle	Thor Delta #139
End of life

Out of service	24 Jun 1983
Cause	Battery failure
Technical data

Specifications

Mass at launch	25.8 kg
Stabilization	Passive magnetic
DC power	15 W (NiCd battery)

Beacons: 29.402 MHz 110mW, 435.095 MHz 100 mW, both Morse CW.


 Oscar 09 failure

Also called Phase 3A

End of life

Out of service	23 May 1980
Cause	Launch failure of Ariane L02
Decay	23 May 1980


 Oscar 10

Also called AO-10 or Phase 3B

General

Designation	14129 / 83058B
Launch date	16 Jun 1983
Country of origin	Germany
Mission	Telecommunications
Perigee/Apogee	4007/35442 km
Inclination	27.2°
Period	699.5 min
Launch vehicle	Ariane L06
Mass at launch	155 kg

First amateur satellite with onboard propulsion. The booster bumped Oscar 10 shortly after separation which damaged one or more of its antennas and also caused other internal injuries because the second and subsequent kick motor firings never happended. This left the spacecraft in a lower inclination elliptical orbit. This meant that the bird didn't have the intended operational coverage nor enough solar panel illumination to sustain full operations.

Technical data

Specifications

Prime contractor
Platform
Mass at launch
Mass in orbit
Dimension
Solar array
Stabilization	Magnetorquer
DC power	50 W (2 NiCd batteries)
Design lifetime
General beacon	145.809 MHz (unmodulated carrier)
Engineering beacon	145.987 MHz (switched off)
Mode B uplink	435.030 - 435.180 MHz (SSB, CW)
Mode B downlink	145.825 - 145.975 MHz (SSB, CW, inverting)


 Oscar 13

Also called AO-13 or Phase 3C

General

Designation	19216 / 88051B
Launch date	15 Jun 1988
Country of origin	United States
Mission	Telecommunications
Perigee/Apogee	809/37995 km
Inclination	57.9°
Period	686.6 min
Launch vehicle	Ariane V23

Much improved brother to Oscar 10: it has the ability to automatically select transponders for each mode at different points in its orbit. However problems occured: it had a RUDAK experiment onboard that failed shortly after launch. Also, in June 1993, the 70 cm downlink transmitter ceased to function, putting an end to Mode J and L operation.

Technical data

Specifications

Prime contractor
Platform
Mass at launch	140 kg
Mass in orbit	90 kg
Dimension
Solar array
Stabilization	Magnetorquer
DC power	50 W (NiCd battery)
Design lifetime

Payload power: 145 MHz - 50 W; 435 MHz - 111 W; 2350 MHz - 1.25 W

general beacon	145.812 mhz (psk, cw, rtty)
engineering beacon	145.985 mhz (psk, cw, rtty)
mode b uplink	435.423 - 435.573 mhz (ssb, cw)
mode b downlink	145.825 - 145.975 mhz (ssb, cw, inverting)
general beacon	435.651 mhz (psk, rtty)
engineering beacon	435.677 mhz (psk, rtty)
mode l uplink	1269.351 - 1269.641 mhz (ssb, cw)
mode l downlink	435.715 -  436.005 mhz (ssb, cw, inverting)
mode j uplink	144.423 - 144.473 mhz (ssb, cw)
mode j downlink	435.940 - 435.990 mhz (ssb, cw, inverting)
beacon	2400.325 mhz (psk, rtty)
beacon	2400.664 mhz (psk, rtty)
mode s uplink	435.603 -  435.639 mhz (ssb, cw, fm)
mode s downlink	2400.711 - 2400.747 mhz (ssb, cw, fm)
rudak uplink	1269.710 mhz (inoperative)
rudak downlink	435.677 mhz (inoperative)

The beacon output alternates between CW, 50 baud RTTY and 400 bps PSK. Beacon transmissions contain satellite engineering data and bulletins from ground control.


 Program: OSO

Orbiting Solar Observatory

American Sun observation program


Program: OSO

OSO 1

OSO 2

OSO C destroyed by Thor Delta #33

OSO 3

OSO 4

OSO 5

OSO 6

OSO 7

OSO 8


 OSO 1

General

Designation	00255 / 62006A
Launch date	7 Mar 1962
Country of origin	United States
Mission	Scientific: Sun observation
Perigee/Apogee	522/553 km
Inclination	32.8°
Period	95.3 min
Launch vehicle	Thor Delta #8
End of life

Decay	8 Oct 1981


 OSO 2

General

Designation	00987 / 65007A
Launch date	3 Feb 1965
Country of origin	United States
Mission	Scientific: Sun observation
Perigee/Apogee	294/306 km
Inclination	32.8°
Period	90.5 min
Launch vehicle	Thor Delta #29
End of life

Decay	9 Aug 1989


 OSO 3

General

Designation	02703 / 67020A
Launch date	8 Mar 1967
Country of origin	United States
Mission	Scientific: Sun observation
Perigee/Apogee	546/570 km
Inclination	32.8°
Period	95.8 min
Launch vehicle	Thor Delta #46
End of life

Decay	4 Apr 1982


 OSO 4

General

Designation	03000 / 67100A
Launch date	18 Oct 1967
Country of origin	United States
Mission	Scientific: Sun observation
Perigee/Apogee	552/555 km
Inclination	32.9°
Period	95.7 min
Launch vehicle	Thor Delta #53
End of life

Decay	15 Jun 1982


 OSO 5

General

Designation	03663 / 69006A
Launch date	22 Jan 1969
Country of origin	United States
Mission	Scientific: Sun observation
Perigee/Apogee	538/559 km
Inclination	33°
Period	95.6 min
Launch vehicle	Thor Delta #64
End of life

Decay	2 Apr 1984


 OSO 6

General

Designation	04065 / 69068A
Launch date	9 Aug 1969
Country of origin	United States
Mission	Scientific: Sun observation
Perigee/Apogee	489/554 km
Inclination	32.9°
Period	95.1 min
Launch vehicle	Thor Delta #72
End of life

Decay	7 Mar 1981


 OSO 7

General

Designation	05491 / 71083A
Launch date	29 Sep 1971
Country of origin	United States
Mission	Scientific: Sun observation
Perigee/Apogee	326/572 km
Inclination	33.1°
Period	93.5 min
Launch vehicle	Thor Delta #85
End of life

Decay	9 Jul 1974


 OSO 8

General

Designation	07970 / 75057A
Launch date	21 Jun 1975
Country of origin	United States
Mission	Scientific: Sun observation
Perigee/Apogee	539/553 km
Inclination	32.9°
Period	95.6 min
Launch vehicle	Thor Delta #112
Mass at launch	1064 kg
End of life

Decay	9 Jul 1986


 Program: OTS

Orbital Test Satellite

European experimental telecommunication program decided by the CEPT (Conférence Européenne des Postes et Télécommunications) with the EBU.


Program: OTS

OTS 1

OTS 2


OTS' specifications

Prime contractor	British Aerospace (now MMS)
Platform	OTS
Mass at launch	865 kg
Mass in orbit	444 kg
Dimension	2.4 x 2.1 x 1.7 m
Solar array	9.3 m span
Stabilization	3 axis
DC power	BOL: 750 W EOL: 555 W
Design lifetime	3 years
Phone circuits	6000


OTS' Ku-band (downlink in 11 GHz)

Module A

Main transponders	4
Backup transponders
Power	20 W
Bandwidth	2 of 40 MHz 2 of 120 MHz
Coverage	40 MHz: European beam A 120 MHz: spot beam
Polarization	linear H/V
Module B

Main transponders	2
Backup transponders
Power	20 W
Bandwidth	5 MHz
Coverage	European beam B
Polarization	circular L/R


 OTS 1

End of life

Out of service	13 Sep 1977 (Friday 13th!)
Cause	Launch failure of a Thor Delta #134
Technical data

Specifications

Ku-band


 OTS 2

General

Designation	10855 / 78044A
Launch date	11 May 1978
Country of origin	Europe
Mission	Telecommunications
Geostationary orbit	10°E
Launch vehicle	Thor Delta #141
End of life

Out of service	Jan 1991
Technical data

Specifications

Ku-band


 Program: OV

Orbiting Vehicle

American program

Each OV1 payload had its own propulsion module. Some OV1 missions carried also a suborbital payload (FIRE 1 & 2, ABRES 6, SSP 29)


Program: OV

OV 1-02

OV 1-04

OV 1-05

OV 1-08

OV 1-09

OV 1-10

OV 1-13

OV 1-14

OV 1-19

OV 1-21

OV 2-1

OV 2-3

OV 2-5

OV 3-1

OV 3-2

OV 3-3

OV 3-4

OV 5-5

OV 5-6

OV 5-9


 OV 1-02

General

Designation	01613 / 65078A
Launch date	5 Oct 1965
Country of origin	United States
Mission
Perigee/Apogee	406/2731 km
Inclination	144.2°
Period	117.5 min
Launch vehicle	Atlas D
Launch site	Vandenberg


 OV 1-04

General

Designation	02121 / 66025A
Launch date	30 Mar 1966
Country of origin	United States
Mission
Perigee/Apogee	884/1008 km
Inclination	144.5°
Period	104 min
Launch vehicle	Atlas D
Launch site	Vandenberg


 OV 1-05

General

Designation	02122 / 66025B
Launch date	30 Mar 1966
Country of origin	United States
Mission
Perigee/Apogee	985/1055 km
Inclination	144.6°
Period	105.6 min
Launch vehicle	Atlas D
Launch site	Vandenberg


 OV 1-08

General

Designation	02324 / 66063A
Launch date	14 Jul 1966
Country of origin	United States
Mission
Perigee/Apogee	985/1022 km
Inclination	144.2°
Period	105.2 min
Launch vehicle	Atlas D
Launch site	Vandenberg
End of life

Decay	4 Jan 1978


 OV 1-09

General

Designation	02610 / 66111A
Launch date	11 Dec 1966
Country of origin	United States
Mission
Perigee/Apogee	471/4626 km
Inclination	99.1°
Period	139.9 min
Launch vehicle	Atlas D
Launch site	Vandenberg


 OV 1-10

General

Designation	02611 / 66111B
Launch date	11 Dec 1966
Country of origin	United States
Mission
Perigee/Apogee	538/604 km
Inclination	93.4°
Period	96.1 min
Launch vehicle	Atlas D
Launch site	Vandenberg


 OV 1-13

General

Designation	03173 / 68026A
Launch date	6 Apr 1968
Country of origin	United States
Mission
Perigee/Apogee	564/9241 km
Inclination	99.9°
Period	198.7 min
Launch vehicle	Atlas F
Launch site	Vandenberg


 OV 1-14

General

Designation	03174 / 68026B
Launch date	6 Apr 1968
Country of origin	United States
Mission
Perigee/Apogee	540/9892 km
Inclination	100°
Period	207.1 min
Launch vehicle	Atlas F
Launch site	Vandenberg


 OV 1-19

General

Designation	03825 / 69025C
Launch date	18 Mar 1969
Country of origin	United States
Mission
Perigee/Apogee	482/5583 km
Inclination	104.8°
Period	151.4 min
Launch vehicle	Atlas F
Launch site	Vandenberg


 OV 1-21

General

Designation	05397 / 71067B
Launch date	7 Aug 1971
Country of origin	United States
Mission
Perigee/Apogee	774/899 km
Inclination	87.6°
Period	101.7 min
Launch vehicle	Atlas F
Launch site	Vandenberg


 OV 2-1

Also called LCS 2

General

Designation	01624 / 65082A
Launch date	15 Oct 1965
Country of origin	United States
Mission
Perigee/Apogee	708/791 km
Inclination	32.6°
Period	99.8 min
Launch vehicle
Launch site	Cape Canaveral
End of life

Decay	27 Jul 1972


 OV 2-3

General

Designation	01863 / 65108A
Launch date	21 Dec 1965
Country of origin	United States
Mission
Perigee/Apogee	167/33662 km
Inclination	26.4°
Period	589.3 min
Launch vehicle
Launch site	Cape Canaveral
End of life

Decay	17 Aug 1975


 OV 2-5

General

Designation	03428 / 68081A
Launch date	26 Sep 1968
Country of origin	United States
Mission
Geostationary orbit
Launch vehicle
Launch site	Cape Canaveral
End of life

Out of service	yes


 OV 3-1

General

Designation	02150 / 66034A
Launch date	22 Apr 1966
Country of origin	United States
Mission
Perigee/Apogee	339/4068 km
Inclination	82.4°
Period	131.9 min
Launch vehicle	Scout #44


 OV 3-2

General

Designation	02517 / 66097A
Launch date	28 Oct 1966
Country of origin	United States
Mission
Perigee/Apogee	319/1599 km
Inclination	81.9°
Period	104.2 min
Launch vehicle	Scout #49
End of life

Decay	29 Sep 1971


 OV 3-3

General

Designation	02389 / 66070A
Launch date	4 Aug 1966
Country of origin	United States
Mission
Perigee/Apogee	348/3132 km
Inclination	81.4°
Period	121.3 min
Launch vehicle	Scout #47


 OV 3-4

General

Designation	02201 / 66052A
Launch date	9 Jun 1966
Country of origin	United States
Mission
Perigee/Apogee	643/4704 km
Inclination	40.9°
Period	142.9 min
Launch vehicle	Scout #44


 OV 5-5

General

Designation	03950 / 69046A
Launch date	23 May 1969
Country of origin	United States
Mission
Perigee/Apogee	59630/69130 km
Inclination	33°
Period	3121.9 min
Launch vehicle
Launch site	Cape Canaveral


 OV 5-6

General

Designation	03951 / 69046B
Launch date	23 May 1969
Country of origin	United States
Mission
Perigee/Apogee	59540/69022 km
Inclination	33.6°
Period	3115.4 min
Launch vehicle
Launch site	Cape Canaveral


 OV 5-9

General

Designation	03952 / 69046C
Launch date	23 May 1969
Country of origin	United States
Mission
Perigee/Apogee	59543/69011 km
Inclination	33.5°
Period	3115.1 min
Launch vehicle
Launch site	Cape Canaveral


 Pacsat

Also called Microsat 1 or AO-16 or Oscar 16

General

Designation	20439 / 90005D
Launch date	22 Jan 1990
Country of origin	United States
Mission	Telecommunications
Perigee/Apogee	781/797 km
Inclination	98.6°
Period	100.6 min
Launch vehicle	Ariane V35
Mass at launch	9 kg

Based on a Amsat-NA Microsat bus

Technical data

S-Band beacon	2401.143 MHz
Uplink	1200 bps Manchester coded (Biphase-L) FSK (FM) AX.25 145.900 145.920 145.940 145.960 MHz
Downlink	1200 bps BPSK (SSB) AX.25, either one of the two frequencies below:
	437.026 MHz (LHCP in northern hemisphere), normal unfiltered PSK 437.051 MHz (RHCP in northern hemisphere), Raised Cosine modulation

Passive magnetic stabilization


 Pageos

Passive Geodetic Earth Orbiting Satellite

General

Designation	02253 / 66056A
Launch date	24 Jun 1966
Country of origin	United States
Mission	Scientific: Geodesy
Perigee/Apogee	2953/5207 km
Inclination	84.4°
Period	177.4 min
Launch vehicle	Thor Agena D
Launch site	Vandenberg

Was an inflatable 30 (or 41?) m diameter aluminum coated mylar balloon weighing 55 kg.

In 1975 the satellite broke up into dozens of pieces... numerous decayed but some remain in orbit. They are of special interest for scientist studying solar radiation pressure (SRP)... because on some orbits, the debris actually gain altitude!


 Program: Palapa

"Palapa" means "unity" is Indonesian

Indonesian telecommunication program

The program was developped in 1975 to solve communications (phone, TV) problems between the numerous islands that compose the country. Two years after the Philippines asked to use to system for their national communications. In 1979 Intelsat recognized the system as a regional operator. In 1993 the operator (Perumtel) was privatized but remains under control.

Master control station is at Daan Magot near Jakarta

Contact

PT Satellit Palapa Indonesia (Satelindo)

Mulia Center, Suite #1201, Ji HR Rasuna Said Kav X6, N° 8, Jakarta 12940, Indonesia

Tel: +62-21-522-9322

Fax: +62-21-522-9320


Program: Palapa

Palapa A1

Palapa A2

Palapa B1

Palapa B2

Palapa B2 P

Palapa B2 R

Palapa B4

Palapa C1

Palapa C2

Palapa C3


Palapa A's C-band

Main transponders	12
Backup transponders
Power
Bandwidth	36 MHz
Coverage	Indonesia
EIRP	34 dBW
Polarization

Satellite designed by Hughes (HS-333), lifetime: 7 years


Palapa B's specifications

Prime contractor	Hughes
Platform	HS-376
Mass at launch	1200 kg
Mass in orbit	628 kg
Diameter	2.16 m
Height	6.83 m deployed
Stabilization	Spin stabilized
DC power	BOL: 1062 W
Design lifetime	8 years


Palapa B's C-band

Main transponders	24
Backup transponders	6
Power	10 W (TWTA)
Bandwidth	36 MHz
Coverage	Indonesia
EIRP	34 dBW
Polarization


 Palapa A1

General

Designation	09009 / 76066A
Launch date	8 Jul 1976
Country of origin	Indonesia
Mission	Telecommunications
Geostationary orbit	83°E
Launch vehicle	Thor Delta #125
End of life

Out of service	1985
Technical data

C-band


 Palapa A2

General

Designation	09862 / 77018A
Launch date	10 Mar 1977
Country of origin	Indonesia
Mission	Telecommunications
Geostationary orbit	77°E
Launch vehicle	Thor Delta #129
End of life

Out of service	1988
Technical data

C-band


 Palapa B1

Palapa Pacific 1

General

Designation	14134 / 83059C
Launch date	18 Jun 1983
Country of origin	Indonesia
Mission	Telecommunications
Geostationary orbit	see below
Launch vehicle	STS 07

This satellite was taken over in 1991 by an affiliate of Satelindo, PT Pasifik Satelit Nusantara (PSN) and renamed Palapa Pacific 1

Location

Begin	End	Position
L: 30 Oct 1982		replaced Palapa A1
Mar 1995	Sep 1995	134°E, inclined
End of life

Out of service	Oct 1995
Cause	drifting but not removed from the belt... probably ran out of fuel!
Technical data

Specifications

C-band


 Palapa B2

General

Designation	14692 / 84011D
Launch date	6 Feb 1984
Country of origin	Indonesia
Mission	Telecommunications
Geostationary orbit
Launch vehicle	STS 11

Launched on a bad orbit (faulty perigee motor) it was retrieved on 12 Nov 1984 by STS 19. This retrieval was financed by the insurance companies, despite the operator's refusal to retrieve it and asked for the insurance money (then used to order Palapa B2P). Some time later the operator changed it's mind and relaunched it as Palapa B2R.

Technical data

Specifications

C-band


 Palapa B2P

General

Designation	17706 / 87029A
Launch date	20 Mar 1987
Country of origin	Indonesia
Mission	Telecommunications
Geostationary orbit	113°E
Launch vehicle	Thor Delta #181
Technical data

Specifications

C-band

C-band EIRP coverage (dBW)


Palapa B2P's EIRP


 Palapa B2R

General

Designation	20570 / 90034A
Launch date	13 Apr 1990
Country of origin	Indonesia
Mission	Telecommunications
Geostationary orbit	108°E
Launch vehicle	Delta 2 #194

It's Palapa B2 retrieved from orbit and modernized.

Technical data

Specifications

C-band

C-band EIRP coverage (dBW)


Palapa B2R's EIRP


 Palapa B4

General

Designation	21964 / 92027A
Launch date	14 May 1992 at 00:40 UT
Country of origin	Indonesia
Mission	Telecommunications
Geostationary orbit	118°E
Launch vehicle	Delta 2 #209

Cost: $56.4 million

Technical data

Specifications

C-band

C-band EIRP coverage (dBW)


Palapa B4's EIRP


 Palapa C1

General

Designation	23779 / 96006A
Launch date	1 Feb 1996 at 1:15 UT
Country of origin	Indonesia
Mission	Telecommunications
Geostationary orbit	113°E
Launch vehicle	Atlas Centaur #98

Launch cost: $90 million. Contract for both Hughes Palapa C: $128 million

GTO: 240 x 89462 km x 21.9°

After testing faulty batteries for Ku-band transponders were discovered. This could lead to the transponders not being marketed. Each transponder is worth $799,000 in revenue a year.

Technical data

EIRP maps

C-band: Asean & New Zealand beam

C-band: Asean beam

C-band: Asia beam

Ku-band

Specifications

Prime contractor	Hughes
Platform	HS-601
Mass at launch	~3000 kg
Mass in orbit	1800 kg
Dimension
Solar array
Stabilization	3 axis
DC power	EOL: 3700 W
Design lifetime	14 years
C-band

Main transponders	24 + 6 (extended)
Backup transponders
Power	standard freq.: 21.5 W (SSPA) extended freq.: 26 W (SSPA)
Bandwidth	36 Mhz
Coverage & EIRP	Indonesia and New Zealand: 36.5 dBW Indonesia: 37 dBW Asia beam (India to Japan): 36 dBW
Polarization	linear
Frequencies	Uplink: 5.925-6.665 GHz Downlink: 3.400-4.200 GHz
Ku-band

Main transponders	4
Backup transponders	2
Power	135 W
Bandwidth	72 MHz
Coverage & EIRP	K1 (Indonesia, Thailand to HongKong): 50 dBW (horizontal) K2 (Japan & Korea): 50 dBW (vertical)
Polarization	linear H/V
Frequencies	Uplink: 13.750-14.490 GHz Downlink: 10.950-11.690 GHz


Palapa C1's Asean & New Zealand beam EIRP


Palapa C1's Asean beam EIRP


Palapa C1's Asia beam EIRP


Palapa C1's Ku band beams EIRP


 Palapa C2

General

Designation
Launch date	planned in spring 1998
Country of origin	Indonesia
Mission	Telecommunications
Geostationary orbit	108°E
Launch vehicle	Ariane
Launch site

HS-601, identical the Palapa C1


 Palapa C3

to be launched (this was an option on the 2 Cs contract)

118°E


 Program: Panamsat

American telecommunication program operated by Alpha Lyracom, the first private company to provide international services. In Sep 1995 PanAmSat becomes the first private company ever to provide global satellite services.

Contact

Alpha Lyracom (PanAmSat)

One Pichwick Plaza, Greenwich, CT 06830, USA

Tel: +1-203-622-6664

Fax: +1-203-622-9163

NASDAQ: SPOT


Program: Panamsat

Panamsat 1

Panamsat 2

Panamsat 3

Panamsat 3R

Panamsat 4

Panamsat 5

Panamsat 6

Panamsat 7

Panamsat 8


 Panamsat 1

Also called PAS 1

General

Designation	19217 / 88051C
Launch date	15 Jun 1988
Country of origin	United States
Mission	Telecommunications
Geostationary orbit	45°W
Launch vehicle	Ariane V23
Technical data

EIRP coverage (dBW)

C-band

Ku-band to Europe

Ku-band to US

Specifications

Prime contractor	GE Astro Space
Platform
Mass at launch	1220 kg
Mass in orbit	708 kg
Dimension	1.63 x 1.32 x 1.9 m
Stabilization	3 axis
DC power	BOL: 1400 W
Design lifetime	11 years

Panamsat 1 is in fact ASC 3, a backup satellite of the ASC program.

C-band

Main transponders	12+6
Backup transponders	2+1
Power	(12+2) transponders of 36 MHz : 8.5 W (SSPA) (6+1) transponders of 72 MHz: 16.2 W (TWTA)
Bandwidth	12 transponders of 36 MHz 6 transponders 72 MHz
Coverage and EIRP	to North America (7, 9, 11, 16 & 18): ? to Central America (8, 10, 12 & 13): 40 dBW to Latin America (1, 3, 5 & 15): 37 dBW to South America (2, 4, 6 & 14): 38 dBW
Polarization	to Latin and South America: linear V to Central and North America: linear H
Transponder frequency chart (GHz)

Horizontal Uplink	Horizontal Downlink	Transponder	Channel	Vertical Downlink	Vertical Uplink
5.945		1	1	3.720
	3.740	7	2		5.965
5.985		2	3	3.760
	3.780	8	4		6.005
6.025		3	5	3.800
	3.820	9	6		6.045
6.065		4	7	3.840
	3.860	10	8		6.085
6.105		5	9	3.880
	3.900	11	10		6.125
6.145		6	11	3.920
	3.940	12	12		6.165
6.185		13A	13	3.960
	3.980	16A	14		6.205
6.225		13B	15	4.000
	4.020	16B	16		6.245
6.265		14A	17	4.040
	4.060	17A	18		6.285
6.305		14B	19	4.080
	4.100	17B	20		6.325
6.345		16A	21	4.120
	4.140	18A	22		6.365
6.385		16B	23	4.160
	4.180	18B	24		6.405
Ku-band (11.5-11.75 GHz)

Main transponders	6
Backup transponders	1
Power	16.2 W (TWTA)
Bandwidth	72 MHz
Coverage and EIRP	Europe (19, 20 & 21): 47 dBW North America (22, 23 & 24): 45 dBW
Polarization	linear H
Transponder frequency chart (GHz)

Horizontal Downlink	Transponder	Vertical Uplink
11.500	19	14.040
11.580	20	14.120
11.660	21	14.200
11.790	22	14.280
11.820	23	14.360
11.900	24	14.440


Panamsat 1's EIRP (C-band)


Panamsat 1's EIRP (Ku-band to Europe)


Panamsat 1's EIRP (Ku-band to US)


 Panamsat 2

Also called PAS 2

General

Designation	23175 / 94040A
Launch date	8 Jul 1994
Country of origin	United States
Mission	Telecommunications
Geostationary orbit	169°E
Launch vehicle	Ariane V65
Technical data

EIRP coverage (dBW)

C-band, Pacific Rim

C-band, Oceania

Ku-band

Specifications

Prime contractor	Hughes
Platform	HS-601
Mass at launch	2920 kg
Mass in orbit
Dimension
Stabilization	3 axis
DC power	5400 W
Design lifetime	15 years
C-band

Main transponders	16
Backup transponders
Power	34 W
Bandwidth	12 transponder of 54 MHz 4 transponder of 64 MHz
Coverage and EIRP	Oceania and Pacific Rim beams (see footprint maps)
Polarization
Transponder frequency chart (GHz)

Horizontal Downlink	Transponder	Vertical Downlink	Bandwidth (MHz)	Beam
	1	3.720	54	Pacific
3.720	2		54	Pacific
	3	3.790	54	Pacific
3.790	4		54	Pacific
	5	3.850	54	Pacific
3.850	6		54	Pacific
	7	3.915	64	Pacific / Oceania
3.915	8		64	Pacific
	9	3.980	54	Pacific
3.980	10		54	Pacific
	11	4.040	54	Pacific / Oceania
4.040	12		54	Pacific
	13	4.100	54	Pacific
4.100	14		54	Pacific
	15	4.165	64	Pacific / Oceania
4.165	16		64	Pacific
Ku-band

Main transponders	16
Backup transponders
Power	63 W
Bandwidth	12 transponder of 54 MHz 4 transponder of 64 MHz
Coverage and EIRP	South Korean beam: 50 dBW and rest of Asia: 42 dBW Chinese beam: 50 dBW Australian beam: 46 dBW
Polarization
Transponder frequency chart (GHz)

Vertical Downlink	Transponder	Horizontal Downlink	Bandwidth (MHz)	Beam
12.281	1		54	China 1
	2	12.281	54	Australia
12.341	3		54	China 2
	4	12.341	54	NE Asia
12.401	5		54	China 1
	6	12.401	54	Australia
12.466	7		64	China 2 / Australia
	8	12.466	64	NE Asia
12.531	9		54	China 1
	10	12.531	54	Australia
12.591	11		54	China 2 / Australia
	12	12.591	54	NE Asia
12.651	13		54	China 1
	14	12.651	54	Australia
12.716	15		64	China 2 / Australia
	16	12.716	64	NE Asia


Panamsat 2's C-band EIRP: Pacific Rim


Panamsat 2's C-band EIRP: Oceania


Panamsat 2's Ku-band EIRP


 Panamsat 3

Also called PAS 3

General

Launch date	1 Dec 1994
Country of origin	United States
Mission	Telecommunications
Geostationary orbit	n/a
Launch vehicle	Ariane V70

Cost: $150 million

End of life

Cause	Launcher failure
Decay	1 Dec 1994
Technical data

Specifications

Prime contractor	Hughes
Platform	HS-601
Mass at launch	2985 kg
Mass in orbit
Dimension	2.84 x 3.53 x 3.6 m
Stabilization	3 axis
DC power	BOL: 5400 W EOL: 4300 W
Design lifetime	15 years
C-band

Main transponders	16
Backup transponders
Power
Bandwidth
Coverage and EIRP	America: 36 dBW Europe and Africa
Polarization
Ku-band

Main transponders	16
Backup transponders
Power
Bandwidth	54 MHz
Coverage and EIRP	Europe: 46.2 dBW North America South America
Polarization


 Panamsat 3R

Also called PAS 3R

General

Designation	23674 / 96002A
Launch date	12 Jan 1996
Country of origin	United States
Mission	Telecommunications
Geostationary orbit	43°W
Launch vehicle	Ariane V82
Technical data

Editorial note: as we don't have Panamsat's Technical User Guide for this satellite (despite our several requests) we can't provide the EIRP maps. Sorry

Specifications

Prime contractor	Hughes
Platform	HS-601
Mass at launch	2918 kg
Mass in orbit
Dimension	2.84 x 3.53 x 3.6 m
Solar array	26.5 m span
Stabilization	3 axis
DC power	BOL: 5400 W EOL: 4300 W
Design lifetime	15 years

It uses Hughes' advanced shaped-reflector technology, which concentrates the satellite's beam over targeted land areas while avoiding uninhabited oceans. Hughes' patented, highly efficient design eliminates the need for multiple feedhorn configurations.

C-band

Main transponders	16
Backup transponders
Power
Bandwidth
Coverage and EIRP	America: 36 dBW Europe and Africa
Polarization
Ku-band

Main transponders	16
Backup transponders
Power
Bandwidth	54 MHz
Coverage and EIRP	Europe: 46.2 dBW North America South America
Polarization


 Panamsat 4

Also called PAS 4

General

Designation	23636 / 95040A
Launch date	3 Aug 1995
Country of origin	United States
Mission	Telecommunications
Geostationary orbit	68.5°E
Launch vehicle	Ariane V76
Technical data

Editorial note: as we don't have Panamsat's Technical User Guide for this satellite (despite our several requests) we can't provide the EIRP maps. Sorry

Specifications

Prime contractor	Hughes
Platform	HS-601
Mass at launch	3043 kg
Dry mass	1671 kg
Mass in orbit
Dimension	2.84 x 3.53 x 3.6 m
Solar array	26.2 m span
Stabilization	3 axis
DC power	BOL: 5400 W EOL: 4300 W
Design lifetime	15 years
C-band

Main transponders	16
Backup transponders
Power
Bandwidth	54 MHz
Coverage and EIRP	Europe and Africa South-East Asia and Australia Singapore and South of China
Polarization
Ku-band

Main transponders	24
Backup transponders
Power
Bandwidth	16 transponders of 27 MHz 8 transponders of 54 MHz
Coverage and EIRP	Europe Middle East Japan: Indonesia: 1 spot to South-Africa for DTH
Polarization


 Panamsat 5

Also called PAS 5

General

Designation
Launch date	planned in 1996
Country of origin	United States
Mission	Telecommunications
Geostationary orbit	79 or 103°W
Launch vehicle	Ariane
Launch site

Will provide up to 225 digital channels for television broadcasting to South America.

Technical data

Specifications

Prime contractor	Space Systems/Loral
Platform	FS 1300
Mass at launch
Mass in orbit
Dimension
Solar array
Stabilization	3 axis
DC power	4000 W
Design lifetime	15 years
C-band

Main transponders	16
Backup transponders
Power
Bandwidth	36 MHz
Coverage
EIRP
Polarization	linear
Ku-band

Main transponders	16
Backup transponders
Power	100 W
Bandwidth	54 MHz
Coverage
EIRP
Polarization	linear


 Panamsat 6

Also called PAS 6

General

Designation
Launch date	planned in 1997
Country of origin	United States
Mission	Telecommunications
Geostationary orbit	79 or 103°W
Launch vehicle	Proton?
Launch site
Technical data

Specifications

Prime contractor	Hughes
Platform	HS-601HP
Mass at launch	3000 kg?
Dry mass
Mass in orbit
Length
Width
Height
Solar array	gallium arsenide
Stabilization	3 axis
DC power	8000 W
Design lifetime	15 years

Will use GaAs (gallium arsenide) solar cells, "advanced" batteries, and xenon-ion stationkeeping thrusters.


 Panamsat 7

Also called PAS 7

General

Designation
Launch date	planned in late-1997
Country of origin	United States
Mission	Telecommunications
Geostationary orbit	68.5°E
Launch vehicle	Ariane 5
Launch site
Mass at launch	~3500 kg

Panamsat gets options for more Arianespace launches

PAS-7 will expand PanAmSat's (PAS 4) southern Southern Africa satellite capacity and will extend its high-power Ku-band satellite coverage for DTH and other applications into Sub-Saharan Africa.

Technical data

C-band

Main transponders	24
Backup transponders
Power
Bandwidth
Coverage
EIRP
Polarization
Ku-band

Main transponders	24
Backup transponders
Power
Bandwidth
Coverage	at least South Africa
EIRP
Polarization


 Panamsat 8

to be launched in 1997 in the Pacific Ocean Region, probably by Proton

Panamsat also plans further satellite in Ka-band to be located at 58 & 79°W for year 2000+


 Pansat

Petite Amateur Navy Satellite

Small, spread-spectrum communication satellite developed by the Naval Postgraduate School (NPS) as an educational project for officer students. Will be a tumbling spacecraft with a weight of 75 kg to be completed in 1996. Probably to be launched by the Shuttle.

The spacecraft will supply direct-sequence, spread-spectrum modulation with an operating center frequency of 436.5 MHz, a bit rate of 9600 bits per second and 4 MB of message storage.

Through use by the amateur radio community PANSAT will supply a means to demonstrate spread-spectrum communications. In addition, PANSAT provides many potential applications for low-cost communications. The low probability-of-intercept would be an important feature for the military in downed-pilot-rescues. The pilot could obtain his/her location through a GPS system and uplink the information to the orbiting satellite at low risk. Examples of civilian uses include emergency rescue and communication to remote areas.

Upload: 435.250 -- 437.750 MHz

Download: 435.250 -- 437.750 MHz


 Program: Parus

Means sail

Russian military navigation program. The constellation is made of 1 satellite per plane on 6 planes spaced by 30°. The first Parus spacecraft was Cosmos 0700, launched in 1974. The system was operational in November 1976. The Tsikada system is a civilian counterpart.

Occupation of the planes

Plane 1	Plane 2	Plane 3	Plane 4	Plane 5	Plane 6
Cosmos 0778	Cosmos 0789	Cosmos 0726	Cosmos 0864	Cosmos 0700	Cosmos 0755
Cosmos 0971	Cosmos 0951	Cosmos 0887	Cosmos 0996	Cosmos 0894	Cosmos 0928
Cosmos 1141	Cosmos 1089	Cosmos 0991	Cosmos 1091	Cosmos 0985	Cosmos 1011
Cosmos 1275	Cosmos 1225	Cosmos 1072	Cosmos 1153	Cosmos 1104	Cosmos 1150
Cosmos 1308	Cosmos 1386	Cosmos 1181	Cosmos 1349	Cosmos 1244	Cosmos 1333
Cosmos 1417	Cosmos 1531	Cosmos 1295	Cosmos 1459	Cosmos 1344	Cosmos 1428
Cosmos 1513	Cosmos 1610	Cosmos 1464	Cosmos 1605	Cosmos 1448	Cosmos 1535
Cosmos 1634	Cosmos 1709	Cosmos 1577	Cosmos 1802	Cosmos 1627	Cosmos 1550
Cosmos 1759	Cosmos 1904	Cosmos 1725	Cosmos 1934	Cosmos 1745	Cosmos 1598
Cosmos 1891	Cosmos 2074	Cosmos 1821	Cosmos 2016	Cosmos 2026	Cosmos 1704
Cosmos 2004	Cosmos 2184	Cosmos 1864	Cosmos 2100	Cosmos 2135	Cosmos 1808
Cosmos 2154	Cosmos 2310	Cosmos 2034	Cosmos 2173	Cosmos 2233	Cosmos 1959
Cosmos 2266		Cosmos 2142	Cosmos 2239		Cosmos 2061
Cosmos 2327		Cosmos 2218			Cosmos 2180
					Cosmos 2279
At least Cosmos 660, 807, 1064, 2321 were Parus satellites but failed to reach the correct orbit.

Technical data

Orbit

Perigee/Apogee	1000 km
Inclination	83°
Period	105 min
Orbital cycle	3 days (same ground tracks every 41 revolutions)
Specifications

Prime contractor	PO Polyot of Omsk
Platform	Musson bus
Mass at launch	~ 700 kg
Mass in orbit
Diameter	~ 2 m (cylinder shape with a long mast)
Height	1.4 m for the first birds, then 2 m (without the mast)
Stabilization
DC power
Design lifetime

Broadcast in VHF and UHF at frequencies around 150 and 400 MHz

Parus, Tsikada, Nadezhda, Kurs,Informator and GEO-IK all use the same basic bus, although Parus has older design systems and tends not to last as long.


 Program: Pegasus

American scientific program


Program: Pegasus

Pegasus 1

Pegasus 2

Pegasus 3


 Pegasus 1

General

Designation	01085 / 65009A
Launch date	16 Feb 1965
Country of origin	United States
Mission	Scientific: observation of meteorites
Perigee/Apogee	510/726 km
Inclination	31.7°
Period	97 min
Launch vehicle
Launch site	Cape Canaveral
End of life

Decay	17 Sep 1978


 Pegasus 2

General

Designation	01381 / 65039A
Launch date	25 May 1965
Country of origin	United States
Mission	Scientific: observation of meteorites
Perigee/Apogee	502/740 km
Inclination	31.7°
Period	97 min
Launch vehicle
Launch site	Cape Canaveral
End of life

Decay	3 Nov 1979


 Pegasus 3

General

Designation	01467 / 65060A
Launch date	30 Jul 1965
Country of origin	United States
Mission	Scientific: observation of meteorites
Perigee/Apogee	441/449 km
Inclination	28.9°
Period	93.4 min
Launch vehicle
Launch site	Cape Canaveral
End of life

Decay	4 Aug 1969


 Pegsat

General

Designation	20546 / 90028A
Launch date	5 Apr 1990
Country of origin	United States
Mission	Scientific: high atmosphere study
Perigee/Apogee	395/500 km
Inclination	94.1°
Period	93.5 min
Launch vehicle	Pegasus #1
Launch site	Vandenberg
Mass at launch	191 kg


 Péole

Means "Préliminaire à EOLE"

General

Designation	04801 / 70109A
Launch date	12 Dec 1970
Country of origin	France
Operator	CNES
Mission	Scientific: high atmosphere study
Perigee/Apogee	634/750 km
Inclination	15°
Period	98.6 min
Launch vehicle	Diamant #6
Mass at launch	58 kg

First geodetic satellite on an equatorial orbit

End of life

Out of service	23 Mar 1972
Decay	16 Jun 1980


 Phase 3D

General

Designation
Launch date	planned in Jun 1997
Country of origin
Mission	Telecommunications
Perigee/Apogee	4000 / 47000 km
Inclination	63.4°
Period
Launch vehicle	Ariane 4
Launch site
Technical data

Specifications

Prime contractor	AMSAT-DL
Platform
Mass at launch	~ 500 kg (including 250 kg fuel)
Mass in orbit
Dimension
Solar array
Stabilization	3 axis
DC power	~ 600 W
Design lifetime

Orbit control with GPS (12 antennas); capable of computing it's own Kepler elements

Uplink frequency chart (MHz)

Uplink	Digital	Analog Passband	Center
15 m	none	21.210 - 21.250	21.230
2 m	145.800 - 145.840	145.840 - 145.990	145.915
70 cm	435.300 - 435.550	435.550 - 435.800	435.675
23 cm (1)	1269.000 - 1269.250	1269.250 - 1269.500	1269.375
23 cm (2)	1268.075 - 1268.350	1268.325 - 1268.575	1268.450
13 cm (1)	2400.100 - 2400.350	2400.350 - 2400.600	2400.475
13 cm (2)	2449.200 - 2446.450	2446.450 - 2446.700	2446.575
6 cm	5668.300 - 5668.550	5668.550 - 5668.800	5668.675
Downlink frequency chart (MHz)

Downlink	Digital	Analog Passband	Center
10 m	29.330
2 m	145.955-145.990	145.805-145.955	145.880
70 cm	435.900-436.200	435.475-435.725	435.600
13 cm	2400.650-2400.950	2400.225-2400.475	2400.350
3 cm	10451.450-10451.750	10451.025-10451.275	10451.150
1.5 cm	24048.450-24048.750	24048.025-24048.275	24048.150
Beacons (MHz)

	Beacon 1	Beacon 2
2 m	none	none
70 cm	435.450	435.850
13 cm	2400.200	2400.600
3 cm	10451.000	10451.400
1.5 cm	24048.000	24048.400


 PMG

Plasma Motor Generator

General

Designation	22701 / 93042B
Launch date	26 Jun 1993 at 13:27 UT
Country of origin	United States
Mission	Tether experiment
Perigee/Apogee	192/850 km
Inclination	26°
Period
Launch vehicle	Delta 2 7925
Launch site	Cape Canaveral

The PMG experiment uses somewhat different hardware from the Seds deployer, although it is for the most part built by the same groups. The PMG tether remained attached to the Delta stage.

PMG was launched with a 500m conducting tether containing a copper cable. The tether deployer and end mass contained a xenon gas dispenser to complete a 0.1 kV electrical circuit through the tether with a 0.3 amp current, in a 6-hour experiment to study space tethers' electrodynamic properties.


 Polaire

End of life

Out of service	5 Dec 1971
Cause	Launch failure (Diamant B4)


 Polar

General

Designation	23802 / 96013A
Launch date	24 Feb 1996 at 11:24 UT
Country of origin	United States
Operator	NASA
Mission	Scientific: magnetosphere study (auroral plasma physics)
Perigee/Apogee
Inclination	86°
Period
Launch vehicle	Delta 2 #33

Launched under the MELVS contract (Medium Expendable Launch Vehicle Services, between NASA and McDonnell Douglas)

Polar is one of two spacecraft in NASA's Global Geospace Science (GGS) mission, which is part of the International Solar-Terrestrial Physics program. Polar and a sister spacecraft, Wind 1, will perform simultaneous, coordinated measurements of key regions of Earth's space environment. Included are observations of the entry and transport of solar plasma over Earth's magnetic poles, imaging of the northern aurora (Northern Lights), and investigations of solar wind properties. Polar was built by Lockheed Martin Astro Space.

Technical data

Polar carries two booms and 6 long wire antennae. In the 'equatorial' plane of the satellite are a pair of antennae spanning 130 meters and, at right angles, another pair of antennae spanning 100 meters. Along the spin axis of the satellite are another pair of antennae with a span of 14 meters. These antennae are used to study electric and magnetic fields for the PWI (Plasma Wave Investigation) and EFI (Electric Field Instrument) experiments. Two larger but shorter (6 m long) booms carry more PWI instruments and the MFE (Magnetic Field Experiment).

Other instruments:

TIMAS (Toroidal Imaging Mass-Angle Spectrograph) to study fluxes of ions as a function of direction

TIDE (Thermal Ion Dynamics Experiment) and PSI (Plasma Source Instrument) which study connections between the polar ionosphere and the magnetotail

VIS (Visible Imaging System) and  UVI (Ultraviolet Imager) which measure auroral emissions.

PIXIE (Polar Ionospheric X-ray Imaging Experiment) studies X-rays produced by energetic electrons in the upper atmosphere.

CAMMICE (Charge and Mass Magnetospheric Ion Composition Experiment) studies the isotopic composition of energetic ions.

CEPPAD (Comprehensive Energetic Particle Pitch Angle Distribution) studies high energy protons and electrons.

(JSR)

Downlink frequency: 2265 MHz


 Pollux

Also called D5A

General

Designation	07801 / 75039A
Launch date	17 May 1975
Country of origin	France
Mission	Technology experimentation
Perigee/Apogee	299/1256 km
Inclination	30°
Period	100.4 min
Launch vehicle	Diamant #11
Mass at launch	37 kg

Must test a hydrazin motor. Counterpart of the first Pollux that was destroy at launch with Castor on 22 May 1973.

End of life

Decay	5 Aug 1975


 Posat

Also called PO-28 or Oscar 28

General

Designation	22829 / 93061G
Launch date	25 Sep 1993
Country of origin	Portugal
Operator	Consorcio Po-SAT of the LNETI (Laboratorio Nacional de Engenhario e Technologia Industrial)
Mission	Telecommunications
Perigee/Apogee	787/803 km
Inclination	98.7°
Period	100.8 min
Launch vehicle	Ariane V59
Mass at launch	45.5 kg

First Portuguese satellite. Built by Surrey's University. Is very similar to Kitsat B with a GPS reception system.

Technical data

Specifications

Prime contractor	SSTL (Surrey Satellite Technology Ltd.)
Platform	SSTL
Mass at launch	50.5 kg
Mass in orbit
Length	352 mm
Width	356 mm
Height	670 mm
Stabilization	gravity gradient
DC power
Design lifetime	5 years
Transponder frequency chart (MHz)

Downlink freq.	Transponder/Beacon	Mode
145.975		JD 9600 bps FSK (Primary)
145.925		JD 9600 bps FSK (Secondary)
Uplink freq.	Transponder/Beacon	Mode
435.075		JD 9600 bps FSK (Primary)
435.050		JD 9600 bps FSK (Secondary)


 Program: Prognoz

Russian scientific program. Designed to study the Sun's activity and its influence on Earth's magnetosphere.


Program: Prognoz

Prognoz 01

Prognoz 02

Prognoz 03

Prognoz 04

Prognoz 05

Prognoz 06

Prognoz 07

Prognoz 08

Prognoz 09

Prognoz 10

Prognoz 11

Prognoz 12


 Prognoz 01

General

Designation	05941 / 72029A
Launch date	14 Apr 1972
Country of origin	CIS
Mission	Scientific: magnetosphere study
Perigee/Apogee	1005/199667 km
Inclination	65°
Period	5782.1 min
Launch vehicle
Launch site	Tyuratam
Mass at launch	845 kg


 Prognoz 02

General

Designation	06068 / 72046A
Launch date	29 Jun 1972
Country of origin	CIS
Mission	Scientific: magnetosphere study
Perigee/Apogee	517/201804 km
Inclination	65.3°
Period	5849.2 min
Launch vehicle
Launch site	Tyuratam
Mass at launch	845 kg

Carries two French experiments (Calypso and Signe) to studies particles from the Sun.

End of life

Decay	15 Dec 1982


 Prognoz 03

General

Designation	06364 / 73009A
Launch date	15 Feb 1973
Country of origin	CIS
Mission	Scientific: magnetosphere study
Perigee/Apogee	590/200000 km
Inclination	65°
Period	5783 min
Launch vehicle
Launch site	Tyuratam
Mass at launch	845 kg


 Prognoz 04

General

Designation	08510 / 75122A
Launch date	22 Dec 1975
Country of origin	CIS
Mission	Scientific: magnetosphere study
Perigee/Apogee	634/199000 km
Inclination	65°
Period	5740 min
Launch vehicle
Launch site	Tyuratam


 Prognoz 05

General

Designation	09557 / 76112A
Launch date	25 Nov 1976
Country of origin	CIS
Mission	Scientific: magnetosphere study
Perigee/Apogee	777/198560 km
Inclination	65.2°
Period	5728 min
Launch vehicle
Launch site	Tyuratam


 Prognoz 06

General

Designation	10370 / 77093A
Launch date	22 Sep 1977
Country of origin	CIS
Mission	Scientific: magnetosphere study
Perigee/Apogee	488/197867 km
Inclination	65°
Period	5688 min
Launch vehicle
Launch site	Tyuratam


 Prognoz 07

General

Designation	11088 / 78101A
Launch date	30 Oct 1978
Country of origin	CIS
Mission	Scientific: magnetosphere study
Perigee/Apogee	472/202627 km
Inclination	64.9°
Period	5881.1 min
Launch vehicle
Launch site	Tyuratam
End of life

Decay	22 Oct 1980


 Prognoz 08

General

Designation	12116 / 80103A
Launch date	25 Dec 1980
Country of origin	CIS
Mission	Scientific: magnetosphere study
Perigee/Apogee	978/197364 km
Inclination	65.8°
Period	5687.8 min
Launch vehicle
Launch site	Tyuratam


 Prognoz 09

General

Designation	14163 / 83067A
Launch date	1 Jul 1983
Country of origin	CIS
Mission	Scientific: radio astronomy and Sun study
Perigee/Apogee	n/a
Inclination	n/a
Period	n/a
Launch vehicle
Launch site	Tyuratam


 Prognoz 10

General

Designation	15661 / 85033A
Launch date	26 Apr 1985
Country of origin	CIS
Mission	Scientific
Perigee/Apogee	5975/194734 km
Inclination	76.8°
Period	5783.7 min
Launch vehicle
Launch site	Tyuratam
End of life

Out of service	Jan 1986


 Prognoz 11

Also called Interbol 1 or Prognoz M2 (SO-M2 no. 512)

General

Designation	23633 / 95039A
Launch date	2 Aug 1995 at 23:59 UT
Country of origin	CIS
Mission	Scientific: magnetosphere study
Perigee/Apogee	505/193064 km
Inclination	63.8°
Period	5472 min
Launch vehicle	Molniya M
Launch site	Plesetsk LC43
Mass at launch	1200 kg

This satellite is the Khvostovoy Zond ("Tail") satellite of Project Interbol, intended to investigate the Earth's geomagnetic tail.

On-board science instruments

SKA-1, PROMICS-3, VDP, AMEI-2, CORAL, ALPHA3 (plasma ions)

ELECTRON, (plasma electrons)

MONITOR-3 (solar wind ions with high time resolution)

IFPE (ion and electron flux variations)

MIF-M, FGS-1, FM-31 (magnetometers); OPERA (electric field)

AKR-X (solar radio emission 0.1-1.5 MHz)

RF-15-1 (solar X-rays 2-240 keV)

SKA-2, DOK-2, SOSNA-2, RKA-2 (energetic particles)


 Prognoz 12

Also called Interbol 2 or (SO-M2 no. 511)

This satellite could be launched to complete Prognoz 11 in 1996 if funds are available. This auroral probe should also carry a Magion subsatellite.


 Prospero

Also called X3

General

Designation	05580 / 71093A
Launch date	28 Oct 1971
Country of origin	United Kingdom
Mission	Technology experimentation
Perigee/Apogee	531/1402 km
Inclination	82°
Period	104.4 min
Launch vehicle	Black Arrow #4
Mass at launch	66 kg

Designed and operated by the RAE. Only satellite launched by a British rocket. Tested solar cells.

Technical data

Transmits on 137.56 MHz


 Program: Proton

Soviet heavy satellite program to study cosmic radiations.

Satellites have 4 solar pannels and a 9.7 m span.


Program: Proton

Proton 1

Proton 2

Proton 3

Proton 4


 Proton 1

General

Designation	01466 / 65054A
Launch date	16 Jul 1965
Country of origin	CIS
Mission	Scientific: ionosphere study
Perigee/Apogee	181/578 km
Inclination	63.4°
Period	92.2 min
Launch vehicle	Proton #1
Mass at launch	12.2 t
End of life

Decay	11 Oct 1965


 Proton 2

General

Designation	01701 / 65087A
Launch date	2 Nov 1965
Country of origin	CIS
Mission	Scientific: ionosphere study
Perigee/Apogee	189/608 km
Inclination	63.5°
Period	92.5 min
Launch vehicle	Proton #2
Mass at launch	12.2 t
End of life

Decay	6 Feb 1966


 Proton 3

General

Designation	02290 / 66060A
Launch date	6 Jul 1966
Country of origin	CIS
Mission	Scientific: ionosphere study
Perigee/Apogee	185/594 km
Inclination	63.5°
Period	92.3 min
Launch vehicle	Proton #4
Mass at launch	12.2 t
End of life

Decay	16 Sep 1966


 Proton 4

General

Designation	03544 / 68103A
Launch date	16 Nov 1968
Country of origin	CIS
Mission	Scientific: ionosphere study
Perigee/Apogee	248/477 km
Inclination	51.6°
Period	91.8 min
Launch vehicle	Proton #13
Mass at launch	17 t
End of life

Decay	24 Jul 1969


 Radarsat

General

Designation	23710 / 95059A
Launch date	4 Nov 1995
Country of origin	Canada
Operator	Canadian Space Agency
Mission	Remote sensing
Perigee/Apogee	783/787 km (polar orbit)
Inclination	98.6°
Period	100 min
Launch vehicle	Delta 2 #229
Mass at launch	2750 kg

Launched under the MELVS contract

RADARSAT is a cooperative program between the Canadian Space Agency, NASA and NOAA. The Canadian Space Agency built and operated the satellite; NASA furnished the launch. In exchange, U.S. government agencies will have access to all archived RADARSAT data and have approximately 15% of the satellite's observing time.

The satellite is worth $640 million dollars Canadian and the launch about $50 million.

Radarsat International, Inc. will be the commercial distributor of RADARSAT data worldwide. Lockheed Martin has distribution rights in the United States.

Contact

Canadian Space Agency

Tel: +1-514-926-4436

Fax: +1-514-926-4973

Email: coord@adro.radar1.sp-agency.ca

http://adro.radar1.sp-agency.ca

RadarSat International (RSI)

275 Slater Street, Suite 1203

Ottawa, Ontario K1P5H9

Canada

Tel: +1-613-238-6413

Fax: +1-613-238-5425

Technical data

Specifications

Prime contractor	Spar Aerospace (Canada)
Platform
Mass at launch	3150 kg?
Mass in orbit
Dimension
Solar array	18 m span
Stabilization
DC power	2200 W
Design lifetime	3 years

15 m long x 1.5 m wide Synthetic Aperture C-band Radar

Resolution: between 30 m and 90 m

Downlink frequency: 2230.000 MHz


 Radcal

Also known as P92-1

General

Designation	22698 / 93041A
Launch date	25 Jun 1993 at 23:30 UT
Country of origin	United States
Mission	Radar calibration
Perigee/Apogee	751/884 km
Inclination	89.5°
Period	101.2 min
Launch vehicle	Scout #117
Mass at launch	87 kg

Was built by Defense Systems Inc. for the USAF Space Test Program

Radcal carries a C-band transponder operating on the same frequency as the radars, and a GPS navigation package so that its orbit can be precisely determined. This calibration will allow the Space Command radars to determine orbital positions of other satellites to within a few metres.


 Program: Raduga

Means rainbow

Soviet telecommunication program

The payloads are Statsionar (C-band), Gals (X-band, 7.25-7.75 GHz) and maybe Volna (L-band).


Program: Raduga

Raduga 01 Raduga 02 Raduga 03 Raduga 04 Raduga 05 Raduga 06 Raduga 07 Raduga 08 Raduga 09 Raduga 10 Raduga 11 Raduga 12 Raduga 13 Raduga 14 Raduga 15	Raduga 16 Raduga 17 Raduga 18 Raduga 19 Raduga 20 Raduga 21 Raduga 22 Raduga 23 Raduga 24 Raduga 25 Raduga 26 Raduga 27 Raduga 28 Raduga 29 Raduga 30	Raduga 31 Raduga 32 Raduga 33 Raduga 1-1 Raduga 1-2 Raduga 1-3


Raduga's specifications

Prime contractor	NPO PM
Platform	Raduga
Mass at launch	1965 kg
Diameter
Height
Stabilization	3 axis
DC power	1300 W
Design lifetime	3 to 5 years

No North-South stabilisation. Equipped with X-band transponders.


Raduga's C-band

Main transponders	3
Backup transponders
Power	15 W (TWTA)
Bandwidth	36 MHz
Coverage and EIRP	hemispheric beam (9°x18°): 32 dBW
Polarization	RHCP: downlink LHCP: uplink


 Raduga 01

General

Designation	08513 / 75123A
Launch date	22 Dec 1975
Country of origin	CIS
Mission	Telecommunications
Geostationary orbit	Statsionar-01, 75°E
Launch vehicle	Proton #56
End of life

Out of service	yes
Technical data

Specifications

C-band


 Raduga 02

General

Designation	09416 / 76092A
Launch date	11 Sep 1976
Country of origin	CIS
Mission	Telecommunications
Geostationary orbit	Statsionar-02, 35°E
Launch vehicle	Proton #59
End of life

Out of service	yes
Technical data

Specifications

C-band


 Raduga 03

General

Designation	10159 / 77071A
Launch date	23 Jul 1977
Country of origin	CIS
Mission	Telecommunications
Geostationary orbit	Statsionar-02, 35°E
Launch vehicle	Proton #63
End of life

Out of service	yes
Technical data

Specifications

C-band


 Raduga 04

General

Designation	10987 / 78073A
Launch date	18 Jul 1978
Country of origin	CIS
Mission	Telecommunications
Geostationary orbit	Statsionar-02, 35°E
Launch vehicle	Proton #69
End of life

Out of service	yes
Technical data

Specifications

C-band


 Raduga 05

General

Designation	11343 / 79035A
Launch date	25 Apr 1979
Country of origin	CIS
Mission	Telecommunications
Geostationary orbit	Statsionar-03, 85°E
Launch vehicle	Proton #77
End of life

Out of service	yes
Technical data

Specifications

C-band


 Raduga 06

General

Designation	11708 / 80016A
Launch date	20 Feb 1980
Country of origin	CIS
Mission	Telecommunications
Geostationary orbit	Statsionar-02, 35°E
Launch vehicle	Proton #82
End of life

Out of service	yes
Technical data

Specifications

C-band


 Raduga 07

General

Designation	12003 / 80081A
Launch date	5 Oct 1980
Country of origin	CIS
Mission	Telecommunications
Geostationary orbit	Statsionar-08, 25°O
Launch vehicle	Proton #85
End of life

Out of service	yes
Technical data

Specifications

C-band


 Raduga 08

General

Designation	12351 / 81027A
Launch date	18 Mar 1981
Country of origin	CIS
Mission	Telecommunications
Geostationary orbit	Statsionar-02, 35°E
Launch vehicle	Proton #87
End of life

Out of service	yes
Technical data

Specifications

C-band


 Raduga 09

General

Designation	12618 / 81069
Launch date	30 Jul 1981
Country of origin	CIS
Mission	Telecommunications
Geostationary orbit	??? 25°E
Launch vehicle	Proton #90
End of life

Out of service	yes
Technical data

Specifications

C-band


 Raduga 10

General

Designation	12897 / 81102A
Launch date	9 Oct 1981
Country of origin	CIS
Mission	Telecommunications
Geostationary orbit	Statsionar-02, 35°E
Launch vehicle	Proton #91
End of life

Out of service	yes
Technical data

Specifications

C-band


 Raduga 11

General

Designation	13669 / 82113A
Launch date	26 Nov 1982
Country of origin	CIS
Mission	Telecommunications
Geostationary orbit	Statsionar-02, 35°E
Launch vehicle	Proton #102
Launch site	Tyuratam
End of life

Out of service	yes
Technical data

Specifications

C-band


 Raduga 12

General

Designation	13974 / 83028A
Launch date	8 Apr 1983
Country of origin	CIS
Mission	Telecommunications
Geostationary orbit	Statsionar-03, 85°E
Launch vehicle	Proton #107
End of life

Out of service	yes
Technical data

Specifications

C-band


 Raduga 13

General

Designation	14307 / 83088A
Launch date	25 Aug 1983
Country of origin	CIS
Mission	Telecommunications
Geostationary orbit	Statsionar-09, 45°E
Launch vehicle	Proton #112
End of life

Out of service	yes
Technical data

Specifications

C-band


 Raduga 14

General

Designation	14725 / 84016A
Launch date	15 Feb 1984
Country of origin	CIS
Mission	Telecommunications
Geostationary orbit	Statsionar-03, 85°E
Launch vehicle	Proton #116
End of life

Out of service	yes
Technical data

Specifications

C-band


 Raduga 15

General

Designation	15057 / 84063A
Launch date	22 Jun 1984
Country of origin	CIS
Mission	Telecommunications
Geostationary orbit	Statsionar-15, 128°E
Launch vehicle	Proton #122
End of life

Out of service	yes
Technical data

Specifications

C-band


 Raduga 16

General

Designation	15946 / 85070A
Launch date	8 Aug 1985
Country of origin	CIS
Mission	Telecommunications
Geostationary orbit	Statsionar-09, 45°E
Launch vehicle	Proton#134
End of life

Out of service	yes
Technical data

Specifications

C-band


 Raduga 17

General

Designation	16250 / 85107A
Launch date	15 Nov 1985
Country of origin	CIS
Mission	Telecommunications
Geostationary orbit	Statsionar-02, 35°E
Launch vehicle	Proton #137
End of life

Out of service	yes
Technical data

Specifications

C-band


 Raduga 18

General

Designation	16497 / 86007A
Launch date	17 Jan 1986
Country of origin	CIS
Mission	Telecommunications
Geostationary orbit	Statsionar-08, 25°W
Launch vehicle	Proton #139
End of life

Out of service	yes
Technical data

Specifications

C-band


 Raduga 19

General

Designation	17046 / 86082A
Launch date	25 Oct 1986
Country of origin	CIS
Mission	Telecommunications
Geostationary orbit	Statsionar-10, 170°W
Launch vehicle	Proton #145
End of life

Out of service	yes
Technical data

Specifications

C-band


 Raduga 20

General

Designation	17611 / 87028A
Launch date	19 Mar 1987
Country of origin	CIS
Mission	Telecommunications
Geostationary orbit	Statsionar-03, 85°E
Launch vehicle	Proton #149
End of life

Out of service	yes
Technical data

Specifications

C-band


 Raduga 21

General

Designation	18631 / 87100A
Launch date	10 Dec 1987
Country of origin	CIS
Mission	Telecommunications
Geostationary orbit	see below
Launch vehicle	Proton #159
Location

Begin	End	Position
L: 10 Dec 1987		Statsionar-15, 128°E
?		Statsionar-10, 170°W, inclined
Technical data

Specifications

C-band

EIRP coverage (dBW)


Raduga 21's EIRP


 Raduga 22

General

Designation	19596 / 88095A
Launch date	20 Oct 1988
Country of origin	CIS
Mission	Telecommunications
Geostationary orbit	see below
Launch vehicle	Proton #172
Location

Begin	End	Position
L: 20 Oct 1988		Statsionar-02, 35°E
?		Statsionar-27, 12°E, inclined
Technical data

Specifications

C-band

EIRP coverage (dBW)


Raduga 22's EIRP


 Raduga 23

General

Designation	19928 / 89030A
Launch date	14 Apr 1989
Country of origin	CIS
Mission	Telecommunications
Geostationary orbit	see below
Launch vehicle	Proton #176
Location

Begin	End	Position
L: 14 Apr 1989	Jul 1995	Statsionar-08, 25°W
Sep 1995		Statsionar-09, 45°E
Technical data

Specifications

C-band


 Raduga 1-1

General

Designation	20083 / 89048A
Launch date	21 Jun 1989
Country of origin	CIS
Mission	Telecommunications
Geostationary orbit	Statsionar-20, 70°E, inclined
Launch vehicle	Proton #178
Technical data

Specifications

C-band

EIRP coverage (dBW)


Raduga 1-1's EIRP


 Raduga 24

General

Designation	20367 / 89098A
Launch date	15 Dec 1989
Country of origin	CIS
Mission	Telecommunications
Geostationary orbit	Statsionar-09, 45°E
Launch vehicle	Proton #183
End of life

Out of service	yes
Technical data

Specifications

C-band


 Raduga 25

General

Designation	20499 / 90016A
Launch date	15 Feb 1990
Country of origin	CIS
Mission	Telecommunications
Geostationary orbit	Statsionar-20, 70°E
Launch vehicle	Proton #185
End of life

Out of service	Mar 1995
Cause	Sent to the junk orbit
Technical data

Specifications

C-band


 Raduga 26

General

Designation	21016 / 90112A
Launch date	20 Dec 1990
Country of origin	CIS
Mission	Telecommunications
Geostationary orbit	see below
Launch vehicle	Proton #194
Location

Begin	End	Position
L: 20 Dec 1990		Statsionar-03, 85°E
Feb 1995	...	constantly drifting
Technical data

Specifications

C-band


 Raduga 1-2

General

Designation	21038 / 90116A
Launch date	27 Dec 1990
Country of origin	CIS
Mission	Telecommunications
Geostationary orbit	Statsionar-24, 49°E, inclined
Launch vehicle	Proton #195
Technical data

Specifications

C-band

EIRP coverage (dBW)


Raduga 1-2's EIRP


 Raduga 27

General

Designation	21132 / 91014A
Launch date	28 Feb 1991
Country of origin	CIS
Mission	Telecommunications
Geostationary orbit	see below
Launch vehicle	Proton #197
Location

Begin	End	Position
L: 28 Feb 1991	Aug 1995	Statsionar-15, 128°E
		drifting West
Technical data

Specifications

C-band


 Raduga 28

General

Designation	21821 / 91087A
Launch date	19 Dec 1991
Country of origin	CIS
Mission	Telecommunications
Geostationary orbit	Statsionar-02, 35°E, inclined
Launch vehicle	Proton #204
Technical data

Specifications

C-band

EIRP coverage (dBW)


Raduga 28's EIRP


 Raduga 29

General

Designation	22557 / 93013A
Launch date	25 Mar 1993 at 02:40 UT
Country of origin	CIS
Mission	Telecommunications
Geostationary orbit	Statsionar-27, 12°E
Launch vehicle	Proton #214
Technical data

Specifications

C-band

EIRP coverage (dBW)


Raduga 29's C-band EIRP


 Raduga 30

General

Designation	22836 / 93062A
Launch date	30 Sep 1993 at 17:06 UT
Country of origin	CIS
Mission	Telecommunications
Geostationary orbit	Statsionar-03, 85°E
Launch vehicle	Proton #216
Technical data

Specifications

C-band

EIRP coverage (dBW)


Raduga 30's C-band EIRP


 Raduga 1-3

General

Designation	22981 / 94008A
Launch date	5 Feb 1994
Country of origin	CIS
Mission	Telecommunications
Geostationary orbit	Statsionar-24, 49°E
Launch vehicle	Proton #220
Technical data

Specifications

C-band

EIRP coverage (dBW)


Raduga 1-3's EIRP


 Raduga 31

General

Designation	23010 / 94012A
Launch date	18 Feb 1994 at 07:56 UT
Country of origin	CIS
Mission	Telecommunications
Geostationary orbit	see below
Launch vehicle	Proton #221
Location

Begin	End	Position
L: 18 Feb 1994	Jul 1995	Statsionar-09, 45°E
Mar 1996		83°E
Technical data

Specifications

C-band


 Raduga 32

General

Designation	23448 / 94087A
Launch date	28 Dec 1994 at 11:31 UT
Country of origin	CIS
Mission	Telecommunications
Geostationary orbit	Statsionar-20, 70°E, inclined
Launch vehicle	Proton #231
Technical data

Specifications

C-band

EIRP coverage (dBW)


Raduga 32's C-band EIRP


 Raduga 33

General

Designation	23794 / 96010A
Launch date	19 February 1996
Country of origin	CIS
Mission	Telecommunications
Geostationary orbit	n/a
Launch vehicle	Proton #240

The upper stage (Block-DM2) failed to restart after first burn to circularize the orbit. Thus the satellite remained in GTO. Failure analysis determined that at second ignition of the Block DM, the main engine experienced an emergency commanded shutdown. The probable cause of the failure was a pressure leak in the engine start system. The leak was most likely caused by an inadequate lockwire installation on a start system tube joint nut, which allowed the nut to back off under vibration. Corrective actions include increasing the lockwire diameter and adding a second, redundant lockwire to the affected joint.

End of life

Out of service	19 Feb 1996
Technical data

Specifications

C-band


 Program: Relay

American experimental telecommunication program operated by NASA.


Program: Relay

Relay 1

Relay 2


Relay's specifications

Prime contractor
Platform
Mass at launch	80 kg
Mass in orbit
Length
Width
Height
Stabilization	Spin?
DC power
Design lifetime


Relay's C-band (upload at 1.7 GHz)

Main transponders	1
Backup transponders
Power	10 W
Bandwidth	600 phone circuits
Coverage
EIRP
Polarization


 Relay 1

General

Designation	00503 / 62068A
Launch date	13 Dec 1962
Country of origin	United States
Mission	Telecommunications
Perigee/Apogee	1323/7433 km
Inclination	47.5°
Period	185.1 min
Launch vehicle	Thor Delta #15

Breaks down on 3 Jan 1963 because of an important power demand but could be mended.

End of life

Out of service	February 1965
Technical data

Specifications

C-band


 Relay 2

General

Designation	00737 / 64003A
Launch date	21 Jan 1964
Country of origin	United States
Mission	Telecommunications
Perigee/Apogee	1960/7541 km
Inclination	46.4°
Period	194.7 min
Launch vehicle	Thor Delta #23
Mass at launch	86 kg

Enabled 10 to 70 minutes transmissions

End of life

Out of service	26 Sep 1965
Technical data

Specifications

C-band


 Program: Resurs

Soviet remote sensing satellite program operated by the Priroda ('Nature') center of the Russian Central Geodesy and Cartography Agency (GUGK).

The F2-series satellites had about 1 month lifetime while the F1 series had only half. The results of the mission (films) are sent back to earth in a reentry vehicle.

Resurs F20 is 60th and the last in Resurs-F series. There were 4 types of Resurs-F spacecrafts: three of Resurs-F1 type and Resurs-F2. First Resurs-F1 named Kosmos-1127 was launched at 10:20 UTC on Sep 05, 1979 from LC41 of Plesetsk cosmodrome. First one of Resurs-F2 series (Kosmos-1906) was launched at 11:30 UTC on Dec 26, 1987 from LC16 of Plesetsk. There were launched total 50 spacecrafts of Resurs-F1 types (28 of the 1st type, 6 of the 2nd and 16 of the 3rd) and 10 of Resurs-F2 type. There were also two launch failures at the launch of Resurs-F1 of the 2nd and the 3rd types. So, there were 62 launch attempts of Resurs-F spacecrafts.


Program Resurs

Resurs F01 Resurs F02 Resurs F03 Resurs F04 Resurs F05 Resurs F06 Resurs F07 Resurs F08 Resurs F09 Resurs F10 Resurs F11 Resurs F12 Resurs F13 Resurs F14 Resurs F15 Resurs F16 Resurs F17 Resurs F18 Resurs F19 Resurs F20	Resurs 500 Resurs O1-0 is Cosmos 1484 Resurs O1-1 is Cosmos 1689 Resurs O1-2 is Cosmos 1939 Resurs O1-3


Resurs F1's specifications

Prime contractor	KB Photon
Platform	modified Vostok
Mass at launch	?
Diameter	?
Stabilization	3 axis


Resurs F2's specifications

Prime contractor	KB Photon
Platform	modified Vostok
Mass at launch	6.5 t (capsule 2.5 t)
Diameter	2.3 m
Stabilization	3 axis


Resurs F2's payload

KFA 1000 film camera system

Wavebands	0.57-0.67 µm (visible) 0.67-0.8 µm (near IR)
Resolution	5-10 m
Swath width	60 km
KATE 200

Wavebands	0.5-0.6, 0.6-0.7, 0.7-0.9 µm (visible/near IR)
Resolution	15-30 m
Swath width	180 km

Also equipped with an LK 1000 camera and a MK 4 camera


Resurs O's specifications

Prime contractor	VNII Elektromekaniki
Mass	~1800 kg
Dimensions	6 m long x 1.4 m diameter
Solar array	10 m
Stabilization	3 axis


Resurs O's payload

MSU-M (low resolution - visible and IR)

Wavebands	0.5-0.6 µm, 0.6-0.7 µm, 0.7-0.8 µm, 0.8-1.0 µm
MSU-S (medium resolution - visible and IR)

Wavebands	0.58-0.7 µm, 0.7-1.0 µm
MSU-SK (5-channel visible and IR scanner)

Wavebands	0.5-0.6 µm, 0.6-0.7 µm, 0.7-08 µm, 0.8-1.0 µm, 10.4-12.6 µm
Resolution	150 m (4 channels), 600 m (1 channel)
Swath width	600 km
MSU-E (3-channel steerable push-broom scanner)

Wavebands	0.5-0.67 µm, 0.65-0.8 µm, 0.8-1.0 µm
Resolution	30 m
Swath width	85 km
FRAGMENT (8-channel TV camera)

Wavebands	0.4-2.1 µm


 Resurs F01

General

Designation	20006 / 89038A
Launch date	25 May 1989
Country of origin	CIS
Mission	Remote sensing (F2)
Perigee/Apogee	174/232 km
Inclination	82.3°
Period	88.6 min
Launch vehicle	Soyuz
Launch site	Plesetsk

Carried two Pion subsatellites aimed to air density research which were released. They were built by students at the Korolev Aviation Institute in Kubyshev.

End of life

Decay	17 Jun 1989
Subsatellites

PION 1 (20056 / 89038C) decayed on 23 Jul 1989

PION 2 (20060 / 89038D) decayed on 24 Jul 1989

Technical data

Specifications

Payload


 Resurs F02

General

Designation	20095 / 89049A
Launch date	27 Jun 1989
Country of origin	CIS
Mission	Remote sensing (F1)
Perigee/Apogee	255/269 km
Inclination	82.6°
Period	89.8 min
Launch vehicle	Soyuz
Launch site	Tyuratam
End of life

Decay	11 Jul 1989
Technical data

Specifications


 Resurs F03

General

Designation	20134 / 89055A
Launch date	18 Jul 1989
Country of origin	CIS
Mission	Remote sensing (F2)
Perigee/Apogee	178/214 km
Inclination	82.6°
Period	88.4 min
Launch vehicle	Soyuz
Launch site	Plesetsk

Carried two Pion air density subsatellites

End of life

Decay	8 Aug 1989
Subsatellites

PION 1 (20160 / 89055C) decayed on 19 Sep 1989

PION 2 (20161 / 89055D) decayed on 19 Sep 1989

Technical data

Specifications

Payload


 Resurs F04

General

Designation	20175 / 89063A
Launch date	15 Aug 1989
Country of origin	CIS
Mission	Remote sensing (F2)
Perigee/Apogee	178/226 km
Inclination	82.3°
Period	88.5 min
Launch vehicle
Launch site	Tyuratam
End of life

Decay	14 Sep 1989
Technical data

Specifications

Payload


 Resurs F05

General

Designation	20222 / 89073A
Launch date	6 Sep 1989
Country of origin	CIS
Mission	Remote sensing (F1)
Perigee/Apogee	176/229 km
Inclination	82.3°
Period	88.6 min
Launch vehicle
Launch site	Plesetsk

Carried CAMEX (Carrier for Microgravity Experiment), a German experiment for Kayser Threde

End of life

Decay	22 Sep 1989
Technical data

Specifications


 Resurs F06

General

Designation	20632 / 90047A
Launch date	29 May 1990
Country of origin	CIS
Mission	Remote sensing (F1)
Perigee/Apogee	175/231 km
Inclination	82.4°
Period	88.6 min
Launch vehicle	Soyuz
Launch site	Plesetsk
End of life

Decay	14 Jun 1990
Technical data

Specifications


 Resurs F07

General

Designation	20687 / 90060A
Launch date	17 Jul 1990
Country of origin	CIS
Mission	Remote sensing (F2)
Perigee/Apogee	177/236 km
Inclination	82.3°
Period	88.6 min
Launch vehicle
Launch site	Plesetsk
End of life

Decay	16 Aug 1990
Technical data

Specifications

Payload


 Resurs F08

General

Designation	20754 / 90073A
Launch date	16 Aug 1990
Country of origin	CIS
Mission	Remote sensing (F1)
Perigee/Apogee	176/229 km
Inclination	82.3°
Period	88.5 min
Launch vehicle
Launch site	Plesetsk
End of life

Decay	1 Sep 1990
Technical data

Specifications


 Resurs F09

General

Designation	20794 / 90082A
Launch date	7 Sep 1990
Country of origin	CIS
Mission	Remote sensing (F1)
Perigee/Apogee	177/238 km
Inclination	82.5°
Period	88.7 min
Launch vehicle	Soyuz
Launch site	Plesetsk

Carried a German experiment

End of life

Decay	21 Sep 1990
Technical data

Specifications


 Resurs F10

General

Designation	21313 / 91035A
Launch date	21 May 1991
Country of origin	CIS
Mission	Remote sensing (F2)
Perigee/Apogee	178/242 km
Inclination	82.3°
Period	88.7 min
Launch vehicle
Launch site	Plesetsk
End of life

Decay	20 Jun 1991
Technical data

Specifications

Payload


 Resurs F11

General

Designation	21524 / 91044A
Launch date	28 Jun 1990
Country of origin	CIS
Mission	Remote sensing (F2)
Perigee/Apogee	253/268 km
Inclination	82.3°
Period	89.7 min
Launch vehicle
Launch site	Plesetsk
End of life

Decay	21 Jul 1991
Technical data

Specifications

Payload


 Resurs F12

General

Designation	21611 / 91052A
Launch date	23 Jul 1991
Country of origin	CIS
Mission	Remote sensing (F1)
Perigee/Apogee	178/230 km
Inclination	82.4°
Period	88.6 min
Launch vehicle	Soyuz
Launch site	Plesetsk
End of life

Decay	8 Aug 1991
Technical data

Specifications


 Resurs F13

General

Designation	21664 / 91058A
Launch date	21 Aug 1991
Country of origin	CIS
Mission	Remote sensing (F2)
Perigee/Apogee	178/240 km
Inclination	82.3°
Period	88.7 min
Launch vehicle
Launch site	Plesetsk
End of life

Decay	20 Sep 1991
Technical data

Specifications

Payload


 Resurs F14

General

Designation	21951 / 92024A
Launch date	29 Apr 1992
Country of origin	CIS
Mission	Remote sensing (F2)
Perigee/Apogee	225/230 km
Inclination	82.1°
Period	89.1 min
Launch vehicle	Soyuz
Launch site	Plesetsk
End of life

Decay	29 May 1992
Technical data

Specifications

Payload


 Resurs F15

General

Designation	21998 / 92033A
Launch date	23 Jun 1992
Country of origin	CIS
Mission	Remote sensing (F1)
Perigee/Apogee	177/226 km
Inclination	82.3°
Period	88.5 min
Launch vehicle	Soyuz
Launch site	Plesetsk
End of life

Decay	9 Jul 1992
Technical data

Specifications


 Resurs F16

General

Designation	22093 / 92056A
Launch date	19 Aug 1992
Country of origin	CIS
Mission	Remote sensing (F2)
Perigee/Apogee	178/226 km
Inclination	82.6°
Period	88.6 min
Launch vehicle
Launch site	Plesetsk

Two passive Pion crafts were released on 1st September. Tracking of their decay will allow studies of atmospheric density and radar calibration.

End of life

Decay	4 Sep 1992
Subsatellites

PION 1 (22099 / 92056C) decayed on 25 Sep 1992

PION 2 (22100 / 92056D) decayed on 24 Sep 1992

Technical data

Specifications

Payload


 Resurs F17

General

Designation	22663 / 93033A
Launch date	21 May 1993 at 09:20 UT
Country of origin	CIS
Mission	Remote sensing (F2)
Perigee/Apogee	176/255 km
Inclination	82.6°
Period	88.8 min
Launch vehicle	Soyuz
Launch site	Plesetsk
End of life

Decay	20 Jun 1993
Technical data

Specifications

Payload


 Resurs F18

General

Designation	22696 / 93040A
Launch date	25 Jun 1993 at 08:20 UT
Country of origin	CIS
Mission	Remote sensing (F1)
Perigee/Apogee	173/240 km
Inclination	82.6°
Period	88.6 min
Launch vehicle	Soyuz
Launch site	Plesetsk
End of life

Decay	12 Jul 1993
Technical data

Specifications


 Resurs F19

General

Designation	22777 / 93053A
Launch date	24 Aug 1993 at 10:45 UT
Country of origin	CIS
Mission	Remote sensing (F1)
Perigee/Apogee	174/236 km
Inclination	82.6°
Period	88.6 min
Launch vehicle	Soyuz
Launch site	Plesetsk
End of life

Decay	10 Sep 1993
Technical data

Specifications


 Resurs F20

General

Designation	23672 / 95050A
Launch date	26 Sep 1995 at 11:20 UT
Country of origin	CIS
Mission	Remote sensing (F2)
Perigee/Apogee	231/233 km
Inclination	82.3°
Period	89 min
Launch vehicle	Soyuz U
Launch site	Plesetsk LC43-4
Mass at launch	~6000 kg

Would be the last Resurs F mission

End of life

Cause	Normal end of mission
Decay	26 Oct 1995
Technical data

Specifications

Payload


 Resurs 500

Also called Zvezda Kolumba which means "Columbus Star"

General

Designation	22217 / 92075A
Launch date	15 Nov 1992 at 21:50 UT
Country of origin	CIS
Mission
Perigee/Apogee	177/237 km
Inclination	82.6°
Period	88.6 min
Launch vehicle	Soyuz
Launch site	Plesetsk

Carries objects and messages. After a 6 day flight the capsule decayed in the Pacific. It was then moved to Seattle for thanksgiving Day. This mission is called Europe-America Space Flight 500. It celebrates the international space year, the 500th anniversary of the new world's discovery and must start a cooperation between US and Russia.

Resurs F1 type

End of life

Decay	22 Nov 1992


 Resurs O1-3

General

Designation	23342 / 94074A
Launch date	4 Nov 1994 at 05:46 UT
Country of origin	CIS
Mission	Remote sensing
Perigee/Apogee	660/663 km
Inclination	98°
Period	98 min
Launch vehicle	Zenith 2
Launch site	Tyuratam LC45

Carried Safir R1. The payload costed DM 6 million (half financed by DARA)

Technical data

Specifications

Payload


 REX 2

Also called P94-2

General

Designation	23814 / 96014A
Launch date	9 Mar 1996
Country of origin	United States
Mission	Military: technology
Operator	USAF
Perigee/Apogee	803 x 332 km
Inclination	90°
Period	101 min
Launch vehicle	Pegasus #10 (XL)

The payload, sponsored by USAF Rome Lab, will study ionospheric electron density irregularities that affect radio communications. A secondary experiment will use GPS for on-orbit attitude determination and control.

Built by CTA/SS (formerly DSI)


 Program: Rohini

Indian scientific program


Program: Rohini

Rohini 1A: launch failure

Rohini 1B

Rohini 2

Rohini 3


 Rohini 1B

Also called RS E2

General

Designation	11899 / 80062A
Launch date	18 Jul 1980
Country of origin	India
Mission	Scientific
Perigee/Apogee	307/921 km
Inclination	44.7°
Period	97 min
Launch vehicle	SLV 3 #2
Mass at launch	35 kg

First Indian satellite launched by an Indian rocket

End of life

Decay	20 May 1981


 Rohini 2

Also called RS D1

General

Designation	12491 / 81051A
Launch date	31 May 1981
Country of origin	India
Mission	Scientific
Perigee/Apogee	188/419 km
Inclination	46.2°
Period	90.6 min
Launch vehicle	SLV 3 #3
Mass at launch	38 kg
End of life

Decay	31 May 1981


 Rohini 3

Also called RS D2

General

Designation	14002 / 83033A
Launch date	17 Apr 1983
Country of origin	India
Mission	Scientific
Perigee/Apogee	326/485 km
Inclination	46.6°
Period	92.7 min
Launch vehicle	SLV 3 #4
Mass at launch	41.5 kg
End of life

Decay	17 Apr 1983


Rorsat
 Program: Rorsat

Radar Ocean Reconnaissance Satellite

Russian program part of the Cosmos constellation. Those satellites are observation satellites using a radar powered by a nuclear engine (50 kg uranium). They are designed to monitor activity of foreign navies. They have a short lifetime (3 to 4 months).

32 spacecrafts launched, 2 already decayed!

Rorsat first generation

1967

(127)	Cosmos 0198

1968

(023)	Cosmos 0209

1970

(079)	Cosmos 0367

1971

(025)	Cosmos 0402

(117)	Cosmos 0469

1972

(066)	Cosmos 0516

1973

(108)	Cosmos 0626

1974

(029)	Cosmos 0651

(032)	Cosmos 0654

1975

(024)	Cosmos 0723

(025)	Cosmos 0724

(116)	Cosmos 0785

1976

(103)	Cosmos 0860

(104)	Cosmos 0861

1977

(088)	Cosmos 0952

(090)	Cosmos 0954 (decayed)

Rorsat second generation

Those satellites separate from their fuel core once out of service

1980

(034)	Cosmos 1176

1981

(021)	Cosmos 1249

(037)	Cosmos 1266

(081)	Cosmos 1299

1982

(043)	Cosmos 1365

(052)	Cosmos 1372

(084)	Cosmos 1402 (decayed)

(099)	Cosmos 1412

Rorsat third generation

Those satellites separate from their fuel core once out of service

1984

(069)	Cosmos 1579

(112)	Cosmos 1607

1985

(064)	Cosmos 1670

(075)	Cosmos 1677

1986

(024)	Cosmos 1736

(062)	Cosmos 1771

1987

(052)	Cosmos 1860

(101)	Cosmos 1900 (is leaking coolant (sodium potassium) from its nuclear power source)

1988

(019)	Cosmos 1932


 Rosat

RÖntgen SATellit

General

Designation	20638 / 90049A
Launch date	1 Jun 1990
Country of origin	Germany
Operator	DLR (German aerospace research establishment)
Mission	Scientific: X-ray astronomy
Perigee/Apogee	538/553 km
Inclination	53°
Period	95.6 min
Launch vehicle	Delta 2 #195

Designed to produce an all-sky survey of some 100,000 X-ray sources, and first all-sky survey in the extreme ultraviolet (XUV) spectrum using the UK-provided Wide Field Camera.

Technical data

Specifications

Prime contractor	Dornier
Mass at launch	2426 kg
Payload mass	1555 kg
Dimension	2.4 x 2.1 x 4.5 m
Solar array	4.7 x 8.9 m
Stabilization	3 axis
DC power	EOL: 1000 W
Design lifetime	1.5 years
Telemetry - Data	S-band
X-ray telescope

Maximum aperture	835 mm
Focal length	2.4 m
On-axis resolution	1.8 arcsecs
Wavelength	0.6-1 µm

It monitors soft 0.1-2.4 keV X-rays.

Wield Field Camera

Maximum aperture	576 mm
Focal length	525 mm
On-axis resolution	1 arcmin
Wavelength	0.6-3 µm


 RS 15

Also called Radio-Rosto (Rosto is an acronyme for Russian Defense, Sports, and Technical Organization)

General

Designation	23439 / 94085A
Launch date	26 Dec 1994
Country of origin	CIS
Mission	Telecommunications
Perigee/Apogee	1881/2163 km
Inclination	64.8°
Period	128 min
Launch vehicle	Rokot #1

All the electronics onboard the satellite was designed and built by a group of Radio Amateurs from the town of Kaluga (180 km SW of Moscow) under the leaderships of Aleksander Papkov. The work was coordinated and supervised by NILAKT POSTO (aero-cosmic laboratory), Moscow, under the direction of Valentin Yamnikov. Full control of RS 15 as well as RS 10/11 and RS 12/13 is implemented by the RS3A control station at Moscow (headed by Leonid Maksakov).

RS-15 suffered from power supply problems, as it goes off almost immediately upon entering earth eclipse, not to return until is 'sees' sunlight again.

Contact

RS3A

PO Box 59, Moscow 105122 -- Russia

Fax: +7-095-916-2949

Email: rsgroup@olymp.msk.su

Packet: RS3A @ RS3A.MSK.RUS.EU

Technical data

Specifications

Prime contractor
Platform	similar to RS 3 to 8 satellites
Mass at launch	70 kg
Mass in orbit
Diameter	1 m (spherical-like)
Solar array
Stabilization	none
DC power
Design lifetime

On board the satellite, there is a Mode A transponder and two CW beacons, one of which consists of a broadcast bulletin board with 2 kilobytes of storage space. A remote control system and telemetry system also exist on the satellite. RS 15 does not have not orientation or attitude stabilization systems.

Transponders

Beacons	29.3525 MHz (0.4 - 1.2 W) 29.3987 MHz (0.4 - 1.2 W)
Uplink	145.858 - 145.898 MHz (approx. 100 W EIRP)
Downlink	29.354 - 29.394 MHz (up to 5 W)


 Ryusei

Also called OREX (Orbital Re-entry Experiment vehicle)

General

Designation	22978 / 94007A
Launch date	3 Feb 1994
Country of origin	Japan
Operator	NASDA
Mission	Technology
Perigee/Apogee	6828/6829 km
Inclination	30.5°
Period	93.5 min
Launch vehicle	H2 01
End of life

Decay	5 Feb 1994 in the Pacific


 S80T

General

Designation	22078 / 92052C
Launch date	10 Aug 1992
Country of origin	France
Operator	CNES
Mission	Scientific
Perigee/Apogee	1302/1324 km
Inclination	66.1°
Period	111.9 min
Launch vehicle	Ariane V52
Technical data

Specifications

Prime contractor	Club ESIE Espace
Platform	UoSAT
Mass at launch	50 kg
Payload mass	7 kg
Dimension	0.7 x 0.35 x 0.35 m
Stabilization
DC power	Consummation: 41 W
Design lifetime	3 years

Frequencies: uplink: 148 MHz, downlink: 137 MHz


 Program: Safir

Satellite For Information Relay

Program of OHB System (Bremen, Germany) with 6 satellites (3 stand-alone and 3 piggybacked). The 3 satellites are planned in 1997, 1998, 1999

Stand-alone satellites

General

Perigee/Apogee	678/696 km
Inclination	98.4°
Period	98 min
Uplinks	401 MHz
Downlinks	400 MHz
Specifications

Prime contractor
Platform
Mass at launch	55 kg
Mass in orbit
Length	45 cm
Width	45 cm
Height	45 cm
Stabilization
DC power
Design lifetime


Program: Safir

Safir R1: on Resurs O1-3


 Safir 1

General

Designation
Launch date	1997
Country of origin	Germany
Mission	Telecommunications
Perigee/Apogee
Inclination
Period
Launch vehicle
Launch site

Safir 1 will be half financed by DARA


 Program: Sakura

Means "cherry tree"

Japanese telecommunications satellite program. Ka-band transponders are used by NTT

Contact

Telecommunication Satellite Corporation of Japan

2-31-19 Shiba, Minato-ku, Tokyo 105, Japan

Tel: +81-3-3769-6811

Fax: +81-3-3452-7600


Program: Sakura

Sakura 1

Sakura 2A

Sakura 2B

Sakura 3A

Sakura 3B


Sakura 3's specifications

Prime contractor	Mitsubishi Electric Co. with NEC (transponders)
Platform	Mitsubishi
Mass at launch	1099 kg
Mass in orbit	550 kg
Diameter	2.184 m
Height	2.429 m
Stabilization	Spin stabilized
DC power	833 to 750 W (depending on the season)
Design lifetime	7 years


Sakura 3's C-band

Main transponders	2
Backup transponders	1
Power	4 W (TWTA)
Bandwidth	180 MHz
Coverage
EIRP	29 dBW
Polarization


Sakura 3's Ka-band

Main transponders	10
Backup transponders	5
Power	4.2 W (TWTA)
Bandwidth	100 MHz
Coverage
EIRP	37 dBW
Polarization


 Sakura 1

Also called CS 1A

General

Designation	10516 / 77118A
Launch date	15 Dec 1977
Country of origin	Japan
Mission	Telecommunications
Geostationary orbit	135°E
Launch vehicle	Thor Delta #137
Mass at launch	350 kg
End of life

Out of service	yes


 Sakura 2A

Also called CS 2A

General

Designation	13782 / 83006A
Launch date	4 Feb 1983
Country of origin	Japan
Mission	Telecommunications
Geostationary orbit	132°E
Launch vehicle
Launch site	Tanegashima
Mass at launch	350 kg
End of life

Out of service	yes
Technical data

Ka-band 20/30 GHz

Phone circuits	4000


 Sakura 2B

Also called CS 2B

General

Designation	14248 / 83081A
Launch date	5 Aug 1983
Country of origin	Japan
Mission	Telecommunications
Geostationary orbit	136°E
Launch vehicle
Launch site	Tanegashima
Mass at launch	350 kg
End of life

Out of service	yes
Technical data

Ka-band 20/30 GHz

Phone circuits	4000


 Sakura 3A

Also called CS 3A

General

Designation	18877 / 88012A
Launch date	19 Feb 1988
Country of origin	Japan
Mission	Telecommunications
Geostationary orbit	132°E
Launch vehicle	H1
Launch site	Tanegashima
Technical data

Specifications

C-band

Ka-band


 Sakura 3B

Also called CS 3B

General

Designation	19508 / 88086A
Launch date	16 Sep 1988
Country of origin	Japan
Mission	Telecommunications
Geostationary orbit	136°E
Launch vehicle	H1
Launch site	Tanegashima
Technical data

Specifications

C-band

Ka-band


 Program: San Marco

Italian high atmosphere study program


Program: San Marco

San Marco 1

San Marco 2

San Marco 3

San Marco 4

San Marco 5


 San Marco 1

General

Designation	00957 / 64084A
Launch date	15 Dec 1964
Country of origin	Italy
Mission	Scientific: high atmosphere study
Perigee/Apogee	200/846 km
Inclination	37.8°
Period	95.1 min
Launch vehicle	Scout #35
Mass at launch	115 kg
End of life

Decay	13 Sep 1965


 San Marco 2

General

Designation	02761 / 67038A
Launch date	26 Apr 1967
Country of origin	Italy
Mission	Scientific: high atmosphere study
Perigee/Apogee	219/741 km
Inclination	2.9°
Period	94.2 min
Launch vehicle	Scout #52
Mass at launch	128 kg
End of life

Decay	14 Oct 1967


 San Marco 3

General

Designation	05176 / 71036A
Launch date	24 Apr 1971
Country of origin	Italy
Mission	Scientific: high atmosphere study
Perigee/Apogee	222/707 km
Inclination	3.2°
Period	93.8 min
Launch vehicle	Scout #72
Mass at launch	161 kg
End of life

Decay	29 Nov 1971


 San Marco 4

General

Designation	07154 / 74009A
Launch date	18 Feb 1974
Country of origin	Italy
Mission	Scientific: high atmosphere study
Perigee/Apogee	270/875 km
Inclination	2.9°
Period	96.1 min
Launch vehicle	Scout #85
Mass at launch	164 kg
End of life

Decay	4 May 1976


 San Marco 5

General

Designation	19013 / 88026A
Launch date	25 Mar 1988
Country of origin	Italy
Mission	Scientific: high atmosphere study
Perigee/Apogee	268/625 km
Inclination	3°
Period	93.5 min
Launch vehicle	Scout #109
Mass at launch	235 kg

Designed by Rome's university

End of life

Decay	6 Dec 1988


 Sara

General

Designation	21578 / 91050E
Launch date	17 Jul 1991
Country of origin	France
Mission	Scientific: radio astronomy
Perigee/Apogee	755/764 km
Inclination	98.4°
Period	100 min
Launch vehicle	Ariane V44
Mass at launch	28 kg

Must study Jupiter's radio environment. Its signals are received at Nancay (Meudon?), France

Technical data

Specifications

Prime contractor	Club ESIEE Espace (built by students)
Mass at launch	28 kg
Mass in orbit	20 kg
Design lifetime	11 years

Telemetry beacon: 145.955 MHz, 300 bps FSK, FM


 Program: Sarsat

Search And Rescue Satellite Aided Tracked

International cooperation program with the United States, Canada, France and since 1979 the CIS which made its Cospas system compatible.

Mission: search and rescue of persons and boats in distress. The service started on 1 Sep 1982. In 1995 28 earth stations and 15 control centers in 16 countries were operational.

The system uses beacons operating at 121.5 MHz and at 406 MHz (and 243 MHz?). Polar orbiting satellites can detect and localize beacons whereas geostationary satellites can't localize them. Thus beacons to work with geostationary birds have to include a GPS receptor.

Satellites carrying a Sarsat-Cospas payload

83082	NOAA 08 (EOL)

84123	NOAA 09

87022	Goes 7

88089	NOAA 11

89050	Nadezhda 1

90017	Nadezhda 2

91019	Nadezhda 3

92041	Insat 2A

93048	Insat 2B

94022	Goes 8

94041	Nadezhda 4

94082	Luch 0

94089	NOAA 14

95025	Goes 9

Future satellites:

Nadezhda 5

NOAA 15


 Program: Satcom

Also called RCA (former owner)

American telecommunication program operated by GE Americom.

Contact

GE Americom

4 Research Way, Princeton, NJ 08540, USA

Tel: +1-609-987-4200

Fax: +1-609-987-4495

NYSE: GE


Program: Satcom

Satcom 1

Satcom 1R

Satcom 2

Satcom 2R

Satcom 3

Satcom 3R

Satcom 4

Satcom C1

Satcom C3

Satcom C4

Satcom K1

Satcom K2


Satcom 1 & 2's C-band

Main transponders	24
Backup transponders
Power
Bandwidth	36 MHz
Coverage
EIRP	32 dBW
Polarization


Satcom K's specifications

Prime contractor	GE Astro Space
Platform	GE 4000
Mass at launch	1930 kg
Mass in orbit	1050 kg
Dimension	1.7 x 2.13 x 1.52 m
Solar array	19.3 m
Stabilization	3 axis
DC power	BOL: 3000 W
Design lifetime	10 year


Satcom K's Ku-band

Main transponders	16
Backup transponders	4
Power	47 W (TWTA)
Bandwidth	54 MHz
Coverage
EIRP	48 dBW
Polarization	linear H/V


Satcom C3 & C4's EIRP


 Satcom 1

General

Designation	08479 / 75117A
Launch date	13 Dec 1975
Country of origin	United States
Mission	Telecommunications
Geostationary orbit	80°W
Launch vehicle	Thor Delta #118
Mass at launch	465 kg
End of life

Out of service	yes
Technical data

C-band


 Satcom 1R

Also called Satcom 6

General

Designation	13984 / 83030A
Launch date	11 Apr 1983
Country of origin	United States
Mission	Telecommunications
Geostationary orbit	see below
Launch vehicle	Thor Delta #167
Launch site	Cape Canaveral
Location

Begin	End	Position
L: 11 Apr 1983		139°W
< May 1992	May 1992 >	131°W
End of life

Out of service	yes
Technical data

Specifications

Prime contractor	GE Astro Space
Platform	GE 3000
Mass at launch	1120 kg
Mass in orbit	approx. 600 kg
Length	1.63 m
Width	1.32 m
Height	0.99 m
Solar array	14.33 m span
Stabilization	3 axis
DC power
Design lifetime	10 years
C-band

Main transponders	24
Backup transponders	4
Power	8.5 W
Bandwidth	36 MHz
Coverage
EIRP	36 dBW
Polarization	linear H/V


 Satcom 2

General

Designation	08774 / 76029A
Launch date	26 Mar 1976
Country of origin	United States
Mission	Telecommunications
Geostationary orbit	see below
Launch vehicle	Thor Delta #121
Launch site	Cape Canaveral
End of life

Out of service	yes
Location

Begin	End	Position
L: 26 Mar 1976		119°W
1984		72°W
Technical data

C-band


 Satcom 2R

Also called Satcom 7

General

Designation	14328 / 83094A
Launch date	8 Sep 1983
Country of origin	United States
Mission	Telecommunications
Geostationary orbit	72°W
Launch vehicle	Thor Delta #172
Launch site	Cape Canaveral
End of life

Out of service	Mar 1995
Cause	Sent to the junk orbit
Technical data

Specifications

Prime contractor	GE Astro Space
Platform	GE 3000
Mass at launch	1120 kg
Mass in orbit	approx. 600 kg
Length	1.63 m
Width	1.32 m
Height	0.99 m
Solar array	14.33 m
Stabilization	3 axis
DC power
Design lifetime	10 year
C-band

Main transponders	24
Backup transponders	4
Power	8.5 W
Bandwidth	36 MHz
Coverage
EIRP	36 dBW
Polarization	linear H/V

Transponder frequency chart


 Satcom 3

General

Designation	11635 / 79101A
Launch date	7 Dec 1979
Country of origin	United States
Mission	Telecommunications
Geostationary orbit	n/a
Launch vehicle	Thor Delta #150
Launch site	Cape Canaveral
End of life

Out of service	7 Dec 1979
Cause	Satellite failure


 Satcom 3R

General

Designation	12967 / 81114A
Launch date	20 Nov 1981
Country of origin	United States
Mission	Telecommunications
Geostationary orbit	131°W
Launch vehicle	Thor Delta #158
Launch site	Cape Canaveral
End of life

Out of service	yes
Technical data

Specifications

Prime contractor	GE Astro Space
Platform	GE 3000
Mass at launch	1070 kg
Mass in orbit	approx. 600 kg
Length	1.6 m
Width	1.27 m
Height	1.29 m
Solar array	11.2 m span
Stabilization	3 axis
DC power
Design lifetime	10 years
C-band

Main transponders	18+6
Backup transponders	3+1
Power	(18+3) transponders of 5.5 W (6+1) transponders of 8.5 W
Bandwidth	36 MHz
Coverage
EIRP	37 dBW
Polarization	linear H/V


 Satcom 4

General

Designation	13035 / 82004A
Launch date	16 Jan 1982
Country of origin	United States
Mission	Telecommunications
Geostationary orbit	82°W
Launch vehicle	Thor Delta #159
Launch site	Cape Canaveral
End of life

Out of service	yes
Technical data

Specifications

Prime contractor	GE Astro Space
Platform	GE 3000
Mass at launch	1070 kg
Mass in orbit	approx. 600 kg
Length	1.6 m
Width	1.27 m
Height	1.29 m
Solar array	11.2 m span
Stabilization	3 axis
DC power
Design lifetime	10 years
C-band

Main transponders	18+6
Backup transponders	3+1
Power	(18+3) transponders 5.5 W (6+1) transponders 8.5 W
Bandwidth	36 MHz
Coverage
EIRP	37 dBW
Polarization	linear H/V


 Satcom C1

General

Designation	20945 / 90100A
Launch date	20 Nov 1990
Country of origin	United States
Mission	Telecommunications
Geostationary orbit	137°W
Launch vehicle	Ariane V40
Technical data

EIRP coverage (dBW)

Specifications

Prime contractor	GE Astro Space
Platform	GE 3000
Mass dry	517 kg
Mass at launch	1169 kg
Mass in orbit	682 kg
Length	1.63 m
Width	1.32 m
Height	0.99 m
Solar array	14.33 m
Stabilization	3 axis
DC power	BOL: 1390 W
Design lifetime	10 years
Beacons	telemetry: 3.7005 GHz (H), 4.1995 GHz (V) command: 6.4235 GHz (H)
C-band

Main transponders	24
Backup transponders	4
Power	8.5 W (SSPA)
Bandwidth	36 MHz
Coverage & EIRP	Conus: 36 dBW Alaska: 34 dBW Hawaii: 32 dBW
Polarization	linear H/V

Transponder frequency chart


Satcom C1's EIRP


 Satcom C3

General

Designation	22117 / 92060B
Launch date	10 Sep 1992
Country of origin	United States
Mission	Telecommunications
Geostationary orbit	131°W
Launch vehicle	Ariane V53
Technical data

EIRP coverage (dBW)

Specifications

Prime contractor	GE Astro Space
Platform
Mass at launch	1370 kg
Mass in orbit	784 kg
Length	1 m
Width	1.6 m
Height	1.5 m
Solar array	15.1 m span
Stabilization	3 axis
DC power	1400 W
Design lifetime	12 years
C-band

Main transponders	24
Backup transponders
Power	17 W
Bandwidth	36 MHz
Coverage & EIRP	see footprint
Polarization	linear H/V

Transponder frequency chart


 Satcom C4

General

Designation	22096 / 92057A
Launch date	31 Aug 1992
Country of origin	United States
Mission	Telecommunications
Geostationary orbit	135°W
Launch vehicle	Delta 2 #213
Launch site	Cape Canaveral
Technical data

EIRP coverage (dBW)

C-band

Main transponders	24
Backup transponders
Power	17 W
Bandwidth
Coverage
EIRP
Polarization	linear H/V

Transponder frequency chart


 Satcom K1

Also called Satcom Ku 1

General

Designation	16482 / 86003B
Launch date	12 Jan 1986
Country of origin	United States
Mission	Telecommunications
Geostationary orbit	85°W
Launch vehicle	STS 32
Technical data

Specifications

Ku-band

Transponder frequency chart (GHz)

Horizontal Uplink	Horizontal Downlink	Transponder	Vertical Downlink	Vertical Uplink
	11.7290	1		14.0290
14.0585		2	11.7585
	11.7880	3		14.0880
14.1175		4	11.8175
	11.8470	5		14.1470
14.1765		6	11.8765
	11.9060	7		14.2060
14.2350		8	11.9350
	11.9650	9		14.2650
14.2945		10	11.9945
	12.0240	11		14.3240
14.3535		12	12.0530
	12.0830	13		14.3830
14.4125		14	12.1125
	12.1420	15		14.4420
14.4715		16	12.1715


 Satcom K2

Also called Satcom Ku 2

General

Designation	16276 / 85109D
Launch date	28 Nov 1985
Country of origin	United States
Mission	Telecommunications
Geostationary orbit	81°W
Launch vehicle	STS 31
Technical data

Specifications

Ku-band

Transponder frequency chart (GHz)

Horizontal Uplink	Horizontal Downlink	Transponder	Vertical Downlink	Vertical Uplink
	11.7290	1		14.0290
14.0585		2	11.7585
	11.7880	3		14.0880	Spot to Western US
14.1175		4	11.8175
	11.8470	5		14.1470
14.1765		6	11.8765
	11.9060	7		14.2060
14.2350		8	11.9350
	11.9650	9		14.2650
14.2945		10	11.9945
	12.0240	11		14.3240
14.3535		12	12.0530
	12.0830	13		14.3830
14.4125		14	12.1125
	12.1420	15		14.4420
14.4715		16	12.1715


 SAX

Satellite per Astronomia a raggi X

General

Designation
Launch date	planned in Dec 1995
Country of origin	Italy and Netherlands
Mission	Scientic: high energy astrophysics
Perigee/Apogee	~ 600 km circular
Inclination	~ 2°
Period	~ 97 min
Launch vehicle	Atlas 1
Launch site	Cape Canaveral
Contact

http://astro.estec.esa.nl/SA-general/Research/Sax/sax.html

Technical data

Specifications

Prime contractor	Alenia Spazio
Platform
Mass at launch	1400 kg
Payload mass	490 kg
Diameter	2.7 m
Height	3.6 m
Solar array	9 m span (2 panels of 2.6 x 3.5 m)
Stabilization	3 axis
DC power	EOL: 2300 W
Design lifetime	4 years
Payload

4 X-ray concentrator/spectrometers

2 wide-field X-ray cameras (WFC)

large area phoswich detector system

high-pressure gas-scintillation proportional counter

X-ray energy detection range	0.1-300 keV
Field of view	WFC: 20 x 20 deg others: 0.5-1.5 deg
Angular resolution	WFC: 5 arcmin others: ~ 1 arcmin
Telemetry	S-band: command: 2 kbps, telemetry/data: 16/131/917 kbps


 Program: SBS

Satellite Business System, also called CNS (Communication Network Service) or USASAT

Satellite Business Systems was created on 15 Dec 1975 by IBM, Comsat and Aetna Life and Casualty Inc. It was the first private professional satellite digital communications network. In Jul 1984, Comsat left the consortium. In Jul 1985, Satellite Business Systems was sold to MCI; four satellites were then in orbit. Sometime around 1987, the fleet was sold off. SBS 1 and 2 were sold to Comsat, SBS 3 remained with MCI, and SBS 4 was sold to IBM's Satellite Transponder Leasing Corp (STLC) together with the SBS 5 and 6 satellites still on the ground. In Apr 1990, Hughes Communications Inc (HCI) bought STLC from IBM. Sometime later (in 1992?) SBS 3 was sold to Comsat so that currently:

SBS 1, 2 & 3 are owned by Comsat

SBS 4, 5 & 6 are owned by HCI


Program: SBS

SBS 1

SBS 2

SBS 3

SBS 4

SBS 5

SBS 6


 SBS 1

General

Designation	12065 / 80091A
Launch date	15 Nov 1980
Country of origin	United States
Mission	Telecommunications
Geostationary orbit	100°W
Launch vehicle	Thor Delta #153
Launch site	Cape Canaveral
End of life

Out of service	yes


 SBS 2

General

Designation	12855 / 81096A
Launch date	24 Sep 1981
Country of origin	United States
Mission	Telecommunications
Geostationary orbit	see below
Launch vehicle	Thor Delta #156
Launch site	Cape Canaveral
Location

Begin	End	Position
L: 24 Sep 1981
< May 1992	Oct 1993 >	97°W
< Jun 1994	...	71°W, inclined
Technical data

Ku-band

Main transponders	10
Backup transponders
Power	8 transponders of 20 W 2 transponders of 40 W
Bandwidth	43 MHz
Coverage	US
EIRP	43-40 dBW
Polarization	linear H
Transponder frequency chart (GHz)

Horizontal Downlink	Transponder	Vertical Uplink
11.725	1	14.025
11.780	2	14.080
11.823	3	14.123
11.872	4	14.172
11.921	5	14.221
11.970	6	14.270
12.019	7	14.319
12.068	8	14.368
12.117	9	14.417
12.166	10	14.466


 SBS 3

General

Designation	13651 / 82110B
Launch date	11 Nov 1982
Country of origin	United States
Mission	Telecommunications
Geostationary orbit	see below
Launch vehicle	STS 05
Location

Begin	End	Position
L: 11 Nov 1982
< May 1992	May 1992 >	95°W
< May 1994	2 Jun 1995	74°W
End of life

Out of service	2 Jun 1995
Cause	moved to the graveyard
Technical data

Ku-band

Main transponders	10
Backup transponders
Power
Bandwidth
Coverage
EIRP	46 dBW
Polarization


 SBS 4

General

Designation	15235 / 84093B
Launch date	31 Aug 1984
Country of origin	United States
Mission	Telecommunications
Geostationary orbit	see below
Launch vehicle	STS 16
Location

Begin	End	Position
L: 31 Aug 1984		?
< May 1992	May 1992 >	91°W
< Oct 1993		77°W, inclined
Technical data

Specifications

Prime contractor	Hughes
Platform	HS-376
Mass at launch	1241 kg
Mass in orbit	725 kg
Diameter	2.16 m
Height	6.6 m
Stabilization	Spin stabilized
DC power	BOL: 1200 W
Design lifetime	10 years
Ku-band

Main transponders	10
Backup transponders	4
Power	5 transponders of 20 W (TWTA) 5 transponders of 40 W (TWTA)
Bandwidth	43 MHz
Coverage	CONUS
EIRP	46 dBW
Polarization	linear H
Transponder frequency chart (GHz)

Horizontal Downlink	Transponder	Vertical Uplink
11.725	1	14.025
11.780	2	14.080
11.823	3	14.123
11.872	4	14.172
11.921	5	14.221
11.970	6	14.270
12.019	7	14.319
12.068	8	14.368
12.117	9	14.417
12.166	10	14.466


 SBS 5

General

Designation	19484 / 88081B
Launch date	8 Sep 1988
Country of origin	United States
Mission	Telecommunications
Geostationary orbit	123°W
Launch vehicle	Ariane V25
Technical data

Specifications

Prime contractor	Hughes
Platform	HS-376
Mass at launch	1241 kg
Mass in orbit	725 kg
Diameter	2.16 m
Height	6.6 m
Stabilization	Spin stabilized
DC power	BOL: 1200 W
Design lifetime	10 years
Ku-band

Main transponders	14
Backup transponders
Power	4 H transponders: variable 20-40 W (TWTA) 6 H transponders: 20 W (TWTA) 4 V transponders: variable 20-40 W (TWTA)
Bandwidth	H transponders: 43 MHz V transponders: 110 MHz
Coverage	CONUS, Alaska, Hawaii
EIRP max	46 dBW
Polarization	linear H/V
Transponder frequency chart (GHz)

Horizontal Downlink	Transponder	Vertical Uplink
11.725	1	14.025
11.780	2	14.080
11.823	3	14.123
11.872	4	14.172
11.921	5	14.221
11.970	6	14.270
12.019	7	14.319
12.068	8	14.368
12.117	9	14.417
12.166	10	14.466
11.748	11	14.048
11.898	12	14.198
11.994	13	14.294
12.141	14	14.441


 SBS 6

General

Designation	20872 / 90091A
Launch date	12 Oct 1990
Country of origin	United States
Mission	Telecommunications
Geostationary orbit	see below
Launch vehicle	Ariane V39
Location

Begin	End	Position
L: 12 Oct 1990
< May 1992	May 1992 >	99°W
< Oct 1993	15 Oct 1995	95°W
Nov 1995		74°W
Technical data

EIRP coverage (dBW)

Horizontal

Vertical

Specifications

Prime contractor	Hughes
Platform	HS-393
Mass at launch	2478 kg
Mass in orbit	1514 kg
Diameter	3.66 m
Height	10 m deployed
Stabilization	Spin stabilized
DC power	BOL: 2300 W
Design lifetime	10 years
Ku-band

Main transponders	19
Backup transponders	11
Power	41 W (TWTA)
Bandwidth	43 MHz
Coverage	CONUS, Alaska, Hawaii
EIRP max	50 dBW
Polarization	linear H
Transponder frequency chart (GHz)

Horizontal Downlink	Transponder	Vertical Uplink
11.7250	1	14.0250
11.7495	2	14.0495
11.7740	3	14.0740
11.7985	4	14.0985
11.8230	5	14.1230
11.8475	6	14.1475
11.8720	7	14.1720
11.8965	8	14.1965
11.9210	9	14.2210
11.9455	10	14.2455
11.9700	11	14.2700
11.9945	12	14.2945
12.0190	13	14.3190
12.0435	14	14.3435
12.0680	15	14.3680
12.0925	16	14.3925
12.1170	17	14.4170
12.1415	18	14.4415
12.1660	19	14.4660


SBS 6's EIRP (Vertical)


SBS 6's EIRP (Horizontal)


 SCD

Satelite de Coleta de Dados

General

Designation	22490 / 93009B
Launch date	9 Feb 1993
Country of origin	Brazil
Operator	INPE
Mission	Remote sensing
Perigee/Apogee	729/793 km
Inclination	25°
Period	100.1 min
Launch vehicle	Pegasus #3
Launch site	Cape Canaveral

First satellite built by Brazil. Must provide a map of CO² distribution in atmosphere above South America. Will collected and transmit data from 500 ground platforms.


 Score

Signal Communication by Orbiting Relay Experiment

General

Designation	00010 / 58006A
Launch date	18 Dec 1958
Country of origin	United States
Mission	Telecommunications
Perigee/Apogee	185/1484 km
Inclination	32.3°
Period	101.5 min
Launch vehicle	Atlas
Launch site	Cape Canaveral
Mass at launch	70 kg

Broadcast President Eisenhower Christmas wishes that had been recorded during 13 days.

End of life

Decay	21 Jan 1959


 Seasat

General

Designation	10967 / 78064A
Launch date	27 Jun 1978
Country of origin	United States
Mission	Remote sensing
Perigee/Apogee	761/764 km
Inclination	108°
Period	100.1 min
Launch vehicle	Atlas Agena D
Launch site	Vandenberg

Seasat was designed to demonstrate techniques for global monitoring of oceanographic phenomena and features, to provide oceanographic data, and to determine key features of an operational ocean-dynamics monitoring system. The major difference between Seasat and previous Earth observation satellites was the use of active and passive microwave sensors to achieve an all-weather capability.

Dedicated ocean monitoring satellite that carried the first spaceborne synthetic aperture radar (SAR) and other microwave instruments.

End of life

Out of service	10 Oct 1978 (106 days of returning data)
Cause	a short circuit drained all power from its batteries
Technical data

Specifications

Prime contractor	Lockheed
Platform	Agena
Mass at launch	2300 kg
Length	21 m
Stabilization	3 axis (momentum wheel/horizon sensing system)
Design lifetime	2 years

The second stage of the Atlas-Agena launch vehicle served as the satellite bus and provided attitude control, power, guidance, telemetry, and command functions. Attached to the Agena was a sensor module which carried the payload of five microwave instruments and their antennas. Together, the two modules were about 21 meters long with a maximum diameter of 1.5 m without appendages deployed. After burnout of the Agena stage and injection into orbit, Seasat-A weighed 2300 kg. In orbit the satellite appeared to stand on end with the sensor and communications antennas pointing toward Earth and the Agena rocket nozzle and solar panels pointing toward space.

SAR (Synthetic Aperture Radar)

Frequency	1.275 GHz (L-band)
Resolution	25 m
Swath width	100 km

Mission: deep ocean wave pattern imaggery, coastal sea/land interaction, ice and snow imagery

ALT (Radar Altimeter)

Frequency	Ku-band
Accuracy	10 cm

Mission: measure satellite altitude above sea surface, significant wave height at sub-satellite point, establish characteristics of marine geoid

SASS (Seasat-A Satellite Scatterometer) - Wind scatterometer

Frequency	1.275 GHz (L-band)
Accuracy	windspeed +/- 2 m/s; direction better than 20°

Mission: windspeed and direction

SMMR (Scanning Multichannel Microwave Radiometer) (passive)

Frequencies	6.6, 18, 37, 10.7 & 21 GHz (H & V polarization)
Swath width	600 km
Accuracy	ocean surface temperature 2 K ocean surface windspeed 2 m/s

Mission: ocean surface temperature and windspeed, water vapor, icecover, rain rate, propagation corrections for other instruments

VIRR (Visible and IR Radiometer)

Wavebands	0.25-0.73 µm 10.5-12.5 µm
Field of view	2-5 km
Swath width	1900 km

Mission: image feature identification in support of other instruments, thermal images of ocean

Downlink frequency: 2287.5 MHz


 Seastar

General

Designation
Launch date	planned in May 1995
Country of origin
Mission
Perigee/Apogee
Inclination
Period
Launch vehicle	Pegasus
Launch site
Mass at launch

Owned by OSC

Downlink: 1702.5 MHz


 Program: Secor

SEquential COllation of Range

Also called EGRS (Experimental Geodetic Research Satellite)

American geodetic satellites for triangulation


Program: Secor

Secor 01B

Secor 02

Secor 03

Secor 04

Secor 05

Secor 06

Secor 07

Secor 08

Secor 09

Secor 13


 Secor 01B

Also called EGRS 01

General

Designation	00729 / 64001C
Launch date	11 Jan 1964
Country of origin	United States
Mission	Scientific: geodesy
Perigee/Apogee	902/922 km
Inclination	69.9°
Period	103.3 min
Launch vehicle	Thor Agena
Launch site	Vandenberg


 Secor 02

Also called EGRS 2

General

Designation	01250 / 65017B
Launch date	11 Mar 1965
Country of origin	United States
Mission	Scientific: geodesy
Perigee/Apogee	296/1014 km
Inclination	90°
Period	97.9 min
Launch vehicle	Thor Ablestar
Launch site	Vandenberg
End of life

Decay	26 Feb 1968


 Secor 03

Also called EGRS 3

General

Designation	01208 / 65016E
Launch date	9 Mar 1965
Country of origin	United States
Mission	Scientific: geodesy
Perigee/Apogee	897/926 km
Inclination	70.1°
Period	103.2 min
Launch vehicle	Thor Agena
Launch site	Vandenberg


 Secor 04

Also called EGRS 4

General

Designation	01315 / 65027B
Launch date	3 Apr 1965
Country of origin	United States
Mission	Scientific: geodesy
Perigee/Apogee	1266/1311 km
Inclination	90.2°
Period	111.4 min
Launch vehicle
Launch site	Vandenberg


 Secor 05

Also called EGRS 5

General

Designation	01506 / 65063A
Launch date	10 Aug 1965
Country of origin	United States
Mission	Scientific: geodesy
Perigee/Apogee	1137/2416 km
Inclination	69.2°
Period	122.2 min
Launch vehicle	Scout #37


 Secor 06

Also called EGRS 6

General

Designation	02205 / 66051B
Launch date	9 Jun 1966
Country of origin	United States
Mission	Scientific: geodesy
Perigee/Apogee	168/3646 km
Inclination	90°
Period	125 min
Launch vehicle
Launch site	Vandenberg
End of life

Decay	6 Jul 1967


 Secor 07

Also called EGRS 7

General

Designation	02411 / 66077B
Launch date	19 Aug 1966
Country of origin	United States
Mission	Scientific: geodesy
Perigee/Apogee	3671/3700 km
Inclination	89.7°
Period	167.5 min
Launch vehicle
Launch site	Vandenberg


 Secor 08

Also called EGRS 8

General

Designation	02520 / 66089B
Launch date	5 Oct 1966
Country of origin	United States
Mission	Scientific: geodesy
Perigee/Apogee	3673/3709 km
Inclination	90°
Period	167.6 min
Launch vehicle
Launch site	Vandenberg


 Secor 09

Also called EGRS 9

General

Designation	02861 / 67065A
Launch date	29 Jun 1967
Country of origin	United States
Mission	Scientific: geodesy
Perigee/Apogee	3792/3946 km
Inclination	90.1°
Period	172.2 min
Launch vehicle	Thor Burner
Launch site	Vandenberg


 Secor 13

Also called EGRS 13

General

Designation	03891 / 69037B
Launch date	14 Apr 1969
Country of origin	United States
Mission	Scientific: geodesy
Perigee/Apogee	1068/1126 km
Inclination	100°
Period	107.2 min
Launch vehicle	Thor Agena D
Launch site	Vandenberg


 Seds 1

Small Expendable Deployer System

General

Designation	22582 / 93017B
Launch date	30 Mar 1993 at 03:29 UT
Country of origin	United States
Mission	Tether experiment
Operator	NASA
Perigee/Apogee	184/746 km
Inclination	34°
Period
Launch vehicle	Delta 2 #219
Launch site	Cape Canaveral LC17A
Mass at launch	23 kg

The system consisted of a small 10 kg deployer cylinder 33 cm long and a tiny 23 kg satellite (`end mass') of similar size. The satellite was connected to the cylinder by a rope made of Spectra-1000 which was 0.75 mm in diameter and 20 km long. The cylinder remained attached to the Delta second stage rocket in orbit.

Seds was developed and built by NASA-Marshall, the Harvard-Smithsonian Center for Astrophysics, and Tether Applications of San Diego, CA. The end mass was built by NASA-Langley.

End of life

Decay	30 Mar 1993


 Seds 2

Small Expendable Deployer System

General

Designation	23028 / 94016B
Launch date	10 Mar 1994 at 03:40 UT
Country of origin	United States
Mission	Tether experiment
Operator	NASA
Perigee/Apogee	347 / 352 km
Inclination	34.9°
Period
Launch vehicle	Delta 2 #226
Launch site	Cape Canaveral LC17
Mass at launch	23 kg

It is a package attached to the Delta second stage rocket which was to deploy a 20 km tether to compare actual tether dynamics with theoretical models. The end mass behaved as expected and unreeled in 1 h 48 min  to a maximum length of 19.8 km.

Unlike Seds 1 for which the tether was severed after deploy, the tether remained attached to the Delta rocket. The end mass mini-satellite transmitted for 10 hours. On 15 Mar 1995 Seds separated from the tether because of an impact and reentred.

The success of Seds 2 confirms that tether systems can be used to deploy sensors which require a particular orientation to the local vertical, such as atmospheric composition experiments.

End of life

Out of service	15 Mar 1994
Decay	8 May 1994


 SFU

Space Flyer Unit

General

Designation	23521 / 95011A
Launch date	17 Mar 1995
Country of origin	Japan
Mission	Scientific
Perigee/Apogee	467/496 km
Inclination	28.5°
Period	92 min
Launch vehicle	H2 02

SFU carried out materials processing, technology and astronomy experiments. It carried the 0.15 m liquid helium cooled IR Telescope in Space (IRTS), with near and mid infrared spectrometers; a biology experiment studying salamander eggs; an electron density experiment; materials processing furnaces; and technology experiments with solar arrays and an electric thruster. It also carried an experimental platform to test technology for the JEM Exposed Facility planned for the Space Station, and as such it is the first flight element of Japan's Station program.

End of life

Out of service	20 Jan 1996
Cause	Retrieved by STS 72

Downlink frequency: 2263.602 MHz


 Shinsei

Means "new star"

General

Designation	05485 / 71080A
Launch date	28 Sep 1971
Country of origin	Japan
Mission	Scientific: ionosphere study
Perigee/Apogee	872/1866 km
Inclination	32.1°
Period	113.1 min
Launch vehicle	Mu 4S
Launch site	Kagoshima
Mass at launch	66 kg


 Sich 1

Also called Ocean O1

General

Designation	23657 / 95046A
Launch date	31 Aug 1995 at 06:50 UT
Country of origin	Ukraine
Operator	National Space Agency of Ukraine (NKAU)
Mission	Remote sensing
Perigee/Apogee	682/651 km
Inclination	82.5°
Period	98.7 min
Launch vehicle	Cyclone 3
Launch site	Plesetsk LC32

First Ukrainian satellite

Based on the Ocean platform built by the Ukrainian firm NPO Yuzhnoe

Was launched with Fasat Alfa which failed to separate


 Sich 2

To be launched in 1996 by a Zenit 2 from Tyuratam


Signe_3
 Signe 3

General

Designation	10064 / 77049A
Launch date	17 Jun 1977
Country of origin	France
Mission	Scientific: gamma-ray astronomy
Perigee/Apogee	449/522 km
Inclination	50.7°
Period	94.3 min
Launch vehicle
Launch site	Tyuratam
Mass at launch	102 kg
End of life

Decay	20 Jun 1979


Program: Simon Bolivar

Project of the 5 Andean Pact countries (Bolivia, Colombia, Ecuador, Peru and Venezuela) to launch telecommunication satellites. The association has also a 15-year agreement with the Intelsat system, offering them rented transponders at preferential rates.

The group could first lease a satellite in orbit before launching a new model with C- and Ku-band capacity for 50 transponders. The cost would be $300 million (half of it for the equipment, its insurance and launching)

The satellite has three possible lines of orbit, at 103, 106 and 109 longitude west, but the Mexican Solidaridad 1 is in orbit at 109.2 degrees west, a path which could seriously interfere with the Simon Bolivar.

The Andean telecommunications companies have been dreaming of having their own satellite for nearly 20 years. The plan produced the "Condor" project in the 1980's, but severe economic crises in several regional nations brought all this to a halt.

This project was revived under the name "Simon Bolivar," with the proposal adapted as a non-governmental multinational business open to different types of international participation, especially funding.


 Program: Sinosat

GEO telecom program to be operated by Sino Satellite Communications (joint venture of CASC and People's Bank of China)

1 satellite (and 2 options) to be built by the EurasSpace joint venture of Daimler-Benz Aerospace and China Aerospace Corp (CASC). Some capacity is for the People's Bank VSAT network. To be launched by a LM 3C in Jun 1997

C-band

Main transponders	16
Backup transponders
Power	16 W
Bandwidth	36 MHz
Coverage	China, Hong Kong and Taiwan
EIRP
Polarization
Ku-band

Main transponders	6
Backup transponders
Power	55 W
Bandwidth	54 MHz
Coverage	China, Hong Kong and Taiwan
EIRP
Polarization


 Program: Sirio

Satellite Italiano Ricerca Industriale Operativa

Italian program


Program: Sirio

Sirio 1

Sirio 2


 Sirio 1

General

Designation	10294 / 77080A
Launch date	25 Aug 1977
Country of origin	Italy
Mission
Geostationary orbit
Launch vehicle	Thor Delta #133
Launch site	Cape Canaveral
Mass at launch	218 kg or 398?
End of life

Out of service	yes


 Sirio 2

End of life

Out of service	10 Sep 1982
Cause	Launch failure of Ariane L05

420 kg satellite aimed for meteorology


 Sirius 1

General

Old name	BSB 1
Country	Sweden
Mission	Direct TV
Geostationary orbit	5.2°E

NSAB is owned 50% by Teracom Svensk Rundradio and 50% by Swedish Space Corporation.

Contact

NSAB (Nordiska Satellitaktiebolaget) c/o Teracom Svensk Rundradio

Box 17666, S-11892 STOCKHOLM, Sweden

Tel: + 46 8 671 20 00

Fax: +46 8 671 20 01

Technical data

Specifications

Ku-band

EIRP coverage (dBW)


Sirius 1's EIRP


 Sirius 2

General

Designation
Launch date	planned in 1997
Country of origin	Sweden
Operator	NSAB & GE Capital Satellites-Europe
Mission
Geostationary orbit	5°E
Launch vehicle	Ariane
Launch site

Operated by NSAB (Nordiska Satellitaktiebolaget) a joint venture by Teracom Svensk Rundradio and Swedish Space Corporation, and GE Capital Satellites-Europe, a subsidiary of GE Capital Satellites International itself a subsidiary of GE Americom

Technical data

Specifications

Prime contractor	Aerospatiale
Platform	Spacebus 3000
Mass at launch	2900 kg
Mass in orbit
Dimension
Solar array
Stabilization
DC power
Design lifetime	15 years
Ku-band for NSAB

Main transponders	16
Backup transponders
Power
Bandwidth
Coverage & EIRP	Spot for scandinavia: 60 dBW
Polarization
Ku-band for GE Capital Satellites-Europe

Main transponders	16
Backup transponders
Power
Bandwidth
Coverage & EIRP	Europe wide: 50 dBW Northern and Central Europe: 50 dBW
Polarization


 Skipper

General

Designation	23752 / 95072B
Launch date	28 Dec 1995 at 06:45 UT
Country of origin	United States
Mission	Scientific
Perigee/Apogee	804/813 km
Inclination	98.6°
Period	101 min
Launch vehicle	Molniya M
Launch site	Tyuratam
Mass at launch	257 kg
End of life

Out of service	28 Dec 1995
Cause	Failed after deployment because the solar panels were wired to discharge instead of charge.

Joint US-Russian satellite: Utah State University provided the forward instrument section an the Moscow Aviation Institute the satellite bus. Shape is a cylinder, 0.8 m diameter and 1.3 m long.

Utah State University's Space Dynamics laboratory in Logan, Utah is the prime contractor and has already conducted similar bow shock test with sub-orbital rockets in April 1990 and February 1991: Bow Shock Ultraviolet 1 and 2. These tests showed ultraviolet light are generated by the bow shock, but tests at higher altitudes and faster speeds needs to be done.

Skipper is to investigate bow shock emissions and aerothermal chemistry reactions produced in Earth's upper atmosphere by manoeuvering and re-entering missile warheads having velocity profiles similar to those expected from the next generation of fast-burning solid propellant missiles.  Skipper spacecraft is an orbital successor to the suborbital Bow Shock 1 and 2 sounding rocket missions which revealed unexpected date on re-entering warhead signatures and which now require more extended experiment and observation time provided by an orbital test.

Spacecraft will carry instrumentation including three scanning spectrometers, a hydrazine thruster system and a photometer plus instrumentation support systems, attitude control and manoeuvering thrusters and science and engineering telemetry to acquire data from higher altitudes and velocities where significant changes in physical processes associated with re-entering warheads are encountered.

On subsequent revolutions perigee will be gradually reduced through controlled manoeuvres to between 120 km and 130 km, spacecraft traverses through very low perigees being observed to simulate warhead re-entries into Earth's upper atmosphere.  Perigee will be decreased until atmospheric drag threatens to initiate re-entry.


 Program: Skynet

English military program


Program: Skynet

Skynet 1A

Skynet 1B

Skynet 2A

Skynet 2B

Skynet 4A

Skynet 4B

Skynet 4C

Skynet 4D

Skynet 4E

Skynet 4F


Skynet 4's specifications

Prime contractor	British Aerospace (now MMS)
Platform	ECS
Mass at launch	1430 kg (1500 kg for 4D & 4E)
Payload mass	225 kg
Length	2.2 m
Width
Height	2.3 m
Solar array	16 m span
Stabilization	3 axis
DC power	BOL: 1200 W
Design lifetime	7 years


Skynet 4's UHF-band (250-315 MHz)

Main transponders	2
Backup transponders
Power	40 W (50 W for 4D & 4E)
Bandwidth	25 KHz
Coverage	Europe
EIRP


Skynet 4's X-band

Main transponders	4
Backup transponders
Power	40 W (50 W for 4D & 4E)
Bandwidth	60 and 135 MHz (60 and 125 MHz for 4D & 4E)
Coverage	Global
EIRP
Polarization
Frequencies	Downlink: 7.23-7.75 GHz


Skynet 4's EHF-band (42 GHz)

Main transponders	1
Backup transponders
Power
Bandwidth
Coverage
EIRP
Polarization


 Skynet 1A

General

Designation	04250 / 69101A
Launch date	22 Nov 1969
Country of origin	United Kingdom
Mission	Military: telecommunications
Geostationary orbit	see below
Launch vehicle	Thor Delta #74
Launch site	Cape Canaveral
Mass at launch	125 kg
End of life

Out of service	yes


 Skynet 1B

General

Designation	04493 / 70062A
Launch date	19 Aug 1970
Country of origin	United Kingdom
Mission	Military: telecommunications
Geostationary orbit	n/a
Launch vehicle	Thor Delta #80
Launch site	Cape Canaveral
End of life

Out of service	19 Aug 1970
Cause	Remained on transfert orbit


 Skynet 2A

General

Designation	07096 / 74002A
Launch date	19 Jan 1974
Country of origin	United Kingdom
Mission	Military: telecommunications
Geostationary orbit	n/a
Launch vehicle	Thor Delta #100
Launch site	Cape Canaveral
End of life

Out of service	25 Jan 1974
Cause	Placed on a bad orbit (96 km x 3406 km x 37.6°)


 Skynet 2B

General

Designation	07547 / 74094A
Launch date	23 Nov 1974
Country of origin	United Kingdom
Mission	Military: telecommunications
Geostationary orbit	42°E
Launch vehicle	Thor Delta #105
Launch site	Cape Canaveral
Mass at launch	235 kg
End of life

Out of service	yes


 Skynet 4A

General

Designation	20401 / 90001A
Launch date	1 Jan 1990
Country of origin	United Kingdom
Mission	Military: telecommunications
Geostationary orbit	see below
Launch vehicle	Titan 3
Launch site	Cape Canaveral
Location

Begin	End	Position
L: 1 Jan 1990		5°E
Feb 1995		34°W, inclined
Technical data

Specifications

UHF-band

X-band

EHF-band


 Skynet 4B

General

Designation	19687 / 88109A
Launch date	11 Dec 1988
Country of origin	United Kingdom
Mission	Military: telecommunications
Geostationary orbit	see below
Launch vehicle	Ariane V27
Location

Begin	End	Position
L: 11 Dec 1988		7°E
Feb 1995		53°E, inclined
Technical data

Specifications

UHF-band

X-band

EHF-band


 Skynet 4C

General

Designation	20776 / 90079A
Launch date	30 Aug 1990
Country of origin	United Kingdom
Mission	Military: telecommunications
Geostationary orbit	see below
Launch vehicle	Ariane V38
Location

Begin	End	Position
L: 30 Aug 1990
Feb 1995		1.1°W, inclined
Technical data

Specifications

UHF-band

X-band

EHF-band


 Skynet 4D

General

Designation
Launch date	planned in 1997
Country of origin	United Kingdom
Mission	Military: telecommunications
Geostationary orbit
Launch vehicle	Delta
Launch site


 Skynet 4E

General

Designation
Launch date	planned in 3rd quarter of 1998
Country of origin	United Kingdom
Mission	Military: telecommunications
Geostationary orbit
Launch vehicle	Ariane
Launch site
Technical data


 Skynet 4F

General

Designation
Launch date	?
Country of origin	United Kingdom
Mission	Military: telecommunications
Geostationary orbit
Launch vehicle	Ariane
Launch site

Contract value: £130 million including delivery-in-orbit of the satellite, with Ariane launch and operational control and in-orbit testing before turnover.

This satellite is supposed identical to Skynet 4D & 4E


 SME

Solar Mesosphere Explorer

General

Designation	12887 / 81100A
Launch date	6 Oct 1981
Country of origin	United States
Mission	Scientific: high atmosphere study
Perigee/Apogee	335/337 km
Inclination	97.6°
Period	91.3 min
Launch vehicle	Thor Delta #157
Launch site	Vandenberg
Mass at launch	437 kg
End of life

Decay	5 Mar 1991


 SMM

Solar Maximum Mission, also called Solmax

General

Designation	11703 / 80014A
Launch date	14 Feb 1980
Country of origin	United States
Mission	Scientific: Sun observation
Perigee/Apogee	405/408 km
Inclination	28.5°
Period	92.7 min
Launch vehicle	Thor Delta #151
Launch site	Cape Canaveral
Mass at launch	2315 kg

Studied solar eruption in the year of the most important solar activity. First use of the MultiMission Spacecraft bus

Its the first satellite repared in orbit by the shuttle (STS 11)

End of life

Decay	2 Dec 1989


 Program: SMS

Synchronous Meteorological Satellite

American meteorological program that was followed by GOES


Program: SMS

SMS 1

SMS 2


 SMS 1

General

Designation	07298 / 74033A
Launch date	17 May 1974
Country of origin	United States
Mission	Meteorology
Geostationary orbit	see below
Launch vehicle	Thor Delta #102
Launch site	Cape Canaveral
Mass at launch	627 kg

First meteorological geostationary satellite. Used for the Gate experiment: covered the Atlantic and Eastern United States

Location

Begin	End	Position
L: 17 May 1974		45°W
		75°W
1980		132°W
End of life

Out of service	yes


 SMS 2

General

Designation	07648 / 75011A
Launch date	6 Feb 1975
Country of origin	United States
Mission	Meteorology
Geostationary orbit	see below
Launch vehicle	Thor Delta #108
Launch site	Cape Canaveral
Mass at launch	627 kg
Location

Begin	End	Position
L: 6 Feb 1975		125°W
1980		75°W
End of life

Out of service	yes


 Soho

Solar and Heliospheric Observatory

General

Designation	/ 95065A
Launch date	2 Dec 1995
Country of origin	Europe
Operator	ESA/NASA
Mission	Scientific: Sun study
Orbit	Heliosynchronous at L1 Lagrange point (1.5 million km from Earth in the direction of the Sun)
Launch vehicle	Atlas 2AS #96

Designed by ESA with the help of NASA. Part of the International Solar-Terrestrial Physics (ISTP) science initiative. Part of the ESA Solar-Terrestrial Science Program (STSP) which is the first of four Cornestone missions in the ESA Horizon 2000 program. With the 4 Cluster spacecrafts, Soho will investigate the Sun and its influence on the Earth's environment.

Soho will then study the origin of the energy within the sun which reaches the suns surface. Part of this energy is then transported to Earth as solar wind. Soho carries telescopes, spectrometers and coronagraphs to study the atmosphere of the Sun, and particle detectors to study the composition and state of the solar wind. Unlike earlier solar observatories, however, Soho also carries instruments to precisely measure oscillations of the Sun, which can be used to study the interior structure of the Sun - a technique called helioseismology.

The program is worth $1 billion; 45% payed by NASA, the rest by ESA.

Technical data

Specifications

Prime contractor	Matra Marconi Space
Platform
Mass at launch	1850 kg
Payload mass	610 kg
Dimension	3.65 x 3.65 x 3.8 m
Solar array	9.5 m span
Stabilization	3 axis, sun-pointing
DC power	1350 W
Design lifetime	2 years (with consumables for extra 4)
Pointing accuracy	+/- 10 arcsec
Pointing stability	arcsec over 1.5 min, 10 arcsec over 6 months
Telemetry/data	S-band (2245.000 MHz), 220 kbps
Storage capacity	1 Gbit
Helioseismology

GOLF (Global Oscillations at Low Frequencies)

VIRGO (Variability of solar Irradiance and Gravity Oscillations)

MDI/SOI (Michelson Doppler Imager/Solar Oscillations Investigation)

Solar Atmosphere (remote sensing)

SUMER (Solar Ultraviolet Measurements of Emitted Radiation)

CDS (Coronal DIagnostic Spectrometer)

EIT (Extreme UV Imaging Telescope)

UVSC (UV Coronagraph Spectrometer)

LASCO (Large Angle and Spectrometric Coronagraph)

SWAN (Solar Wind Anisotropies)

Solar wind (in situ)

CELIAS (Charge, Element and Isotrope Analysis System)

COSTEP (Comprehensive Suprathermal and Energetic Particle analyser)

ERNE (Energetic and Relativistic Nuclei and Electron experiment)


 Solar A

Also called Yohkoh

General

Designation	21694 / 91062A
Launch date	30 Aug 1991
Country of origin	Japan
Mission
Perigee/Apogee	516/754 km
Inclination	31.3°
Period	97.4 min
Launch vehicle	Mu 3S 2
Launch site	Kagoshima


 Program: Solidaridad

Mexican telecommunication program operated by SCT. Replaces Morelos


Program: Solidaridad

Solidaridad 1

Solidaridad 2


Solidaridad's specifications

Prime contractor	Hughes
Platform	HS-601
Mass at launch	2740 kg
Mass in orbit	1650 kg
Dimension	2.27 x 2.27 x 2.27 m
Solar array	18.3 m span
Stabilization	3 axis
DC power	3300 W
Design lifetime	14 years


Solidaridad's L-band

Main transponders	1
Backup transponders
Power	100 W
Bandwidth	34 MHz
Coverage
EIRP	45 dBW
Polarization	RHCP


Solidaridad's C-band

Main transponders	18
Backup transponders
Power	10 W (36 MHz) 14 W (72 MHz)
Bandwidth	12 transponders of 36 MHz 6 transponders of 72 MHz (on spot 1)
Coverage & EIRP	Spot 1: 40.5 dBW Spot 2: 37.5 dBW Spot 3: 37.5 dBW
Polarization	linear


Solidaridad's Ku-band

Main transponders	16
Power	42.5 W (TWTA)
Bandwidth	54 MHz
Coverage & EIRP	Spot 4: 47 dBW Spot 5: 46 dBW Spot 6: 45.5 dBW
Polarization	linear


 Solidaridad 1

General

Designation	22911 / 93073A
Launch date	20 Nov 1993
Country of origin	Mexico
Mission	Telecommunications
Geostationary orbit	109.2°W
Launch vehicle	Ariane V61
Technical data

Specifications

L-band

C-band

Ku-band


 Solidaridad 2

General

Designation	23313 / 94065A
Launch date	8 Oct 1994
Country of origin	Mexico
Mission	Telecommunications
Geostationary orbit	113°W
Launch vehicle	Ariane V68
Technical data

Specifications

L-band

C-band

Ku-band

EIRP coverage (dBW)

C-band

Ku-band


Solidaridad 2's C-band EIRP


Solidaridad 2's Ku-band EIRP


 Program: Solrad

American astronomy program operated by US Navy and NASA


Program: Solrad

Solrad 01

Solrad 03

Solrad 06A

Solrad 06B

Solrad 07A

Solrad 07B

Solrad 09

Solrad 10

Solrad 11A

Solrad 11B


 Solrad 01

Also called GREB

General

Designation	00046 / 60007B
Launch date	22 Jun 1960
Country of origin	United States
Mission	Scientific
Perigee/Apogee	590/940 km
Inclination	66.7°
Period	100.1 min
Launch vehicle	Thor Ablestar
Launch site	Cape Canaveral


 Solrad 03

Also called Injun 1

General

Designation	00117 / 61015B
Launch date	29 Jun 1961
Country of origin	United States
Mission	Scientific: ionosphere study
Perigee/Apogee	869/991 km
Inclination	66.8°
Period	103.6 min
Launch vehicle	Thor Ablestar
Launch site	Cape Canaveral


 Solrad 06A

General

Designation	00599 / 63021C
Launch date	15 Jun 1963
Country of origin	United States
Mission
Perigee/Apogee	170/869 km
Inclination	69.9°
Period	95.1 min
Launch vehicle	Thor Agena D
Launch site	Vandenberg
End of life

Decay	1 Aug 1963


 Solrad 06B

Also called GREB 6

General

Designation	01271 / 65016A
Launch date	9 Mar 1965
Country of origin	United States
Mission
Perigee/Apogee	895/926 km
Inclination	70.1°
Period	103.2 min
Launch vehicle	Thor Agena D
Launch site	Vandenberg


 Solrad 07A

General

Designation	00730 / 64001D
Launch date	11 Jan 1964
Country of origin	United States
Mission	Scientific
Perigee/Apogee	900/921 km
Inclination	69.9°
Period	103.2 min
Launch vehicle	Thor Agena
Launch site	Vandenberg


 Solrad 07B

General

Designation	01291 / 65016D
Launch date	9 Mar 1965
Country of origin	United States
Mission	Scientific
Perigee/Apogee	900/928 km
Inclination	70.1°
Period	103.3 min
Launch vehicle	Thor Agena D
Launch site	Vandenberg


 Solrad 09

Also called Explorer 37

General

Designation	03141 / 68017A
Launch date	5 Mar 1968
Country of origin	United States
Mission	Scientific: observation if the sun
Perigee/Apogee	353/433 km
Inclination	59.3°
Period	92.4 min
Launch vehicle	Scout #60
End of life

Decay	16 Nov 1990


 Solrad 10

Also called Explorer 44

General

Designation	05317 / 71058A
Launch date	8 Jul 1971
Country of origin	United States
Mission	Scientific: observation if the sun
Perigee/Apogee	433/632 km
Inclination	51.1°
Period	95.2 min
Launch vehicle	Scout #74
End of life

Decay	15 Dec 1979


 Solrad 11A

General

Designation	08748 / 76023C
Launch date	15 Mar 1976
Country of origin	United States
Mission	Scientific
Perigee/Apogee	118383/119180 km
Inclination	25.7°
Period	7344.3 min
Launch vehicle
Launch site	Cape Canaveral


 Solrad 11B

General

Designation	08749 / 76023D
Launch date	15 Mar 1976
Country of origin	United States
Mission	Scientific
Perigee/Apogee	115720/116645 km
Inclination	25.6°
Period	7116.7 min
Launch vehicle
Launch site	Cape Canaveral


 Solwind

General

Designation	11278 / 79017A
Launch date	24 Feb 1979
Country of origin	United States
Mission	Scientific: high atmosphere study
Perigee/Apogee	310/317 km
Inclination	97.8°
Period	90.8 min
Launch vehicle	Atlas F
Launch site	Vandenberg
End of life

Decay	20 Jul 1992


Program: Spacenet
 Spacenet

American telecommunication program operated by GE Americom, formerly GTE Spacenet Corp.

Contact

GE Americom

4 Research Way, Princeton, NJ 08540, USA

Tel: +1-609-987-4200

Fax: +1-609-987-4495

NYSE: GE


Program: Spacenet

Spacenet 1

Spacenet 2

Spacenet 3

Spacenet 3R


Spacenet's specifications

Prime contractor	GE Astro Space
Platform	GE 3000
Mass at launch	1195 kg
Mass in orbit	692 kg
Dimension	1.63 x 1.32 x 0.99 m
Solar array	14.33 m span
Stabilization	3 axis
DC power	BOL: 1530 W
Design lifetime	10 years


Spacenet's C-band

Main transponders	12+6
Backup transponders	2+1
Power	(12+2) transponders of 8.5 W (TWTA) (6+1) transponders of 16 W (TWTA)
Bandwidth	8.5 W transponders: 36 MHz 16 W transponders: 72 MHz
Coverage
EIRP	36 dBW
Polarization	linear H/V


Spacenet's Ku-band

Main transponders	6
Backup transponders	1
Power	16 W (TWTA)
Bandwidth	72 MHz
Coverage	CONUS
EIRP	44 dBW
Polarization	linear H


 Spacenet 1

General

Designation	14985 / 84049A
Launch date	23 May 1984
Country of origin	United States
Mission	Telecommunications
Geostationary orbit	see below
Launch vehicle	Ariane V09

Was sold by GTE Spacenet to the Chinese and became Chinasat 5. Then the Chinese found an arrangement with Intelsat for 50% of it's capacity. At the same time China provided a Chinese orbital slot at 110.5°E for Intelsat 805.

Location

Begin	End	Position
L: 23 May 1984		102°W
< May 1992	May 1992 >	120°W
Feb 1995	...	115.5°E
Technical data

Specifications

C-band

Ku-band


 Spacenet 2

Also called Satcom SN2

General

Designation	15385 / 84114A
Launch date	10 Nov 1984
Country of origin	United States
Mission	Telecommunications
Geostationary orbit	69°W
Launch vehicle	Ariane V11
Technical data

Specifications

C-band

Ku-band

C-band transponder frequency chart

Ku-band transponder frequency chart (GHz)

Horizontal Downlink	Transponder	Vertical Uplink
11.740	19	14.040
11.820	20	14.120
11.900	21	14.200
11.980	22	14.280
12.060	23	14.360
12.140	24	14.440


 Spacenet 3

End of life

Out of service	13 Sep 1985
Cause	Launch failure: Ariane V15
Technical data

Specifications

C-band

Ku-band


 Spacenet 3R

General

Designation	18951 / 88018A
Launch date	11 Mar 1988
Country of origin	United States
Mission	Telecommunications
Geostationary orbit	87°W
Launch vehicle	Ariane V21
Technical data

Specifications

C-band

Ku-band

C-band transponder frequency chart

Carries at least 1 L-band transponder used by Qualcomm Inc. for a localization service

Ku-band transponder frequency chart (GHz)

Horizontal Downlink	Transponder	Vertical Uplink
11.740	19	14.040
11.820	20	14.120
11.900	21	14.200
11.980	22	14.280
12.060	23	14.360	West spot
12.140	24	14.440	East spot


C-band frequency chart (Spacenet)
 C-band frequency chart (Spacenet) (GHz)

Vertical Uplink	Horizontal Downlink	Transponder	Channel	Vertical Downlink	Horizontal Uplink
	3.720	1	1		5.945
5.965		13L	2	3.740
	3.760	2	3		5.985
6.005		13U	4	3.780
	3.800	3	5		6.025
6.045		14L	6	3.820
	3.840	4	7		6.065
6.085		14U	8	3.860
	3.880	5	9		6.105
6.125		15L	10	3.900
	3.920	6	11		6.145
6.125		15U	12	3.940
	3.960	7	13		6.185
6.205		16L	14	3.980
	4.000	8	15		6.225
6.245		16U	16	4.020
	4.040	9	17		6.265
6.285		17L	18	4.060
	4.080	10	19		6.305
6.325		17U	20	4.100
	4.120	11	21		6.345
6.365		18L	22	4.140
	4.160	12	23		6.385
6.405		18U	24	4.180


 Program: Spaceway

Project of Hughes: geostationary satellites in 5 different slots (25°E, 50°W, 110°W, 175°E). Up to 4 satellites per slot. uplink: 29-30 GHz, downlink: 19.2-20.2 GHz With 48 spots (of 650 km diameter)

It would provide 11520 data circuits

Global cost of the project: $3.2 billion. The first satellite should be launched in 1998, maybe with a Delta 3

Oct 1995: HCI filed an amendment with the Federal Communications Commission to its existing application for SPACEWAY, a planned global interactive "bandwidth-on-demand" data, video and telephony service.  The system, renamed GALAXY/SPACEWAY(TM) expands the original SPACEWAY system to include conventional communication satellite services such as programming distribution on a global basis.


 Program: Spartan

American scientific program. The satellites are reused to carry experiments in space with the Shuttle. 3-axis spacecrafts.

Spartan is managed by NASA-Goddard.


Program: Spartan

Spartan 101-1

Spartan 201-1

Spartan 201-2

Spartan 201-3

Spartan 204-1

Spartan 206-1


 Spartan 101-1

General

Designation	15831 / 85048E
Launch date	20 Jun 1985
Country of origin	United States
Mission	Scientific: X-ray astronomy
Perigee/Apogee	359/395 km
Inclination	28.5°
Period	92.1 min
Launch vehicle	STS 25
End of life

Cause	Retrieved by the Shuttle
Decay	24 Jun 1985


 Spartan 201-1

General

Designation	22623 / 93023B
Launch date	11 Apr 1993 at 06:11 UT
Country of origin	United States
Mission	Scientific: high atmosphere and Sun study
Perigee/Apogee	291/298 km
Inclination	57°
Period	90.4 min
Launch vehicle	STS 56
Mass at launch	1290 kg

It carried an ultraviolet coronagraph and a white light coronagraph for studies of the Sun.

End of life

Cause	Retrieved by the Shuttle
Decay	13 Apr 1993


 Spartan 204-1

General

Designation	23253 / 94059B
Launch date	9 Sep 1994
Country of origin	United States
Mission	Scientific: Sun study
Perigee/Apogee	259/269 km
Inclination	56.9°
Period	89.5 min
Launch vehicle	STS 64

It carried optical instruments to measure the speed and acceleration of the solar wind in the corona.

End of life

Cause	Retrieved by the Shuttle
Decay	20 Sep 1994


 Spartan 201-2

General

Designation	23470 / 95004B
Launch date	7 Feb 1995 at 12:26 UT
Country of origin	United States
Mission	Scientific: astronomy
Perigee/Apogee	310/342 km
Inclination	51.6°
Period	91 min
Launch vehicle	STS 63

The spacecraft carried NRL's FUVIS Far Ultraviolet Imaging Spectrograph which will be used to study the Shuttle environment and make astronomical observations. This is the first Spartan mission to be sponsored by the USAF Space Test Program rather than NASA. It made about 40 hours of observation of Galactic dust clouds.

End of life

Cause	Retrieved by the Shuttle
Decay	9 Feb 1995


 Spartan 201-3

General

Designation	23668 / 95048B
Launch date	8 Sep 1995 at 16.43 UT
Country of origin	United States
Mission	Scientific: astronomy
Perigee/Apogee
Inclination
Period
Launch vehicle	STS 69
Mass at launch	2209 kg

Carried the IEH-1 (International EUV Hitchhiker) built by the Smithsonian Astrophysical Observatory. This includes a solar EUV telescope (SEH), and an Italian-US EUV telescope, UVSTAR, which will observe a variety of astronomical targets in the 500-1250A range. Prime target for this mission is Io plasma torus around Jupiter. Comet 6P/D'Arrest, currently near perihelion, may also be observed. UVSTAR has two 0.3 m telescopes.

The spacecraft also carried the GLO-3 airglow experiment in a canister and the CONCAP materials processing experiment in another canister.

End of life

Cause	Retrieved by the Shuttle
Reentry	18 Sep 1995


 Spartan 206-1

Also called OAST (Office of Aeronautical and Space Technology) Flyer

General

Designation	23763 / 96001B
Launch date	11 Jan 1996
Country of origin	United States
Mission	Scientific: Sun study
Perigee/Apogee	302/311 km
Inclination	28.5°
Period
Launch vehicle	STS 72

Carried an experiment to measure contamination caused by spacecraft outgassing, and a test of a laser-fired explosive separation device to make sure the device doesn't go off accidentally in sunlight. It also carried an amateur radio experiment.

End of life

Cause	Retrieved by the Shuttle
Reentry	20 Sep 1994


 Program: Spas

Shuttle PAllet Satellite

Reusable free-flying multi-purpose platform on which experiments can be carried into space by the space shuttle.


Program: Spas

Spas 1

Spas 2

Spas 3


Spas's specifications

Prime contractor	MBB
Stabilization	3 axis
Total system mass	3600 kg
Payload mass	2000 kg
Length in payload bay	1.7 m
Mission lifetime	4 to 10 days
Electrical energy	up to 70 kWh


Astro Spas's specifications

Prime contractor	MBB
Total system mass	3200-3600 kg
Payload mass	500-2000 kg
Length in payload bay	4.05 m
Width (basic system)	1.75 m
Width (with payload)	2-3 m
Height	4.05 m
Stabilization	3 axis
Mission lifetime	4 to 10 days
Electrical energy	110 kWh (batteries) 30-50 kWh (payload)
Frequency (to Shuttle)	S-band: 2.04885/2.2250 GHz to Shuttle: 16 kbps From Shuttle: 2 kbps


 Spas 1

General

Designation	14142 / 83059F
Launch date	18 Jun 1983
Country of origin	Germany
Mission	Scientific
Perigee/Apogee	295/300 km
Inclination	28.5°
Period	90.5 min
Launch vehicle	STS 07
End of life

Cause	Retrieved by the Shuttle
Decay	24 Jun 1983
Technical data

Specifications


 Spas 2

Also called IBSS

General

Designation	21244 / 91031B
Launch date	28 Apr 1991
Country of origin	United States
Mission	Scientific
Perigee/Apogee	245/255 km
Inclination	57°
Period	89.5 min
Launch vehicle	STS 39
End of life

Cause	Retrieved by the Shuttle
Decay	6 May 1991
Technical data

Specifications


 Spas 3

Also called Orfeus (Orbiting and Retrievable Far and Extreme UV Spectrometer)

General

Designation	22798 / 93058C
Launch date	12 Sep 1993
Country of origin	Germany
Mission	Scientific: Astronomy
Operator	DARA
Perigee/Apogee	301/331 km
Inclination	28.5°
Period	90.9 min
Launch vehicle	STS 51

The main instrument is the 1-meter Orfeus telescope with EUV (400-1150A) and far UV (900-1250A) spectrometers with high spectral resolution. A secondary experiment is the Princeton Interstellar Medium Absorption Profile Spectrograph which studied very fine structure in ultraviolet absorption lines caused by interstellar gas in stellar spectra.

End of life

Cause	Retrieved by the Shuttle
Decay	22 Sep 1993
Technical data

Specifications


 Spas 4

Also called Crista

General

Designation	23341 / 94073B
Launch date	4 Nov 1994
Country of origin	Germany
Mission	Scientific
Perigee/Apogee	296/310 km
Inclination	57°
Period	90.6 min
Launch vehicle	STS 66
Mass at launch	3500 kg

It carried spectraphotometers to monitor gases in the middle atmosphere and lower thermosphere.

End of life

Cause	Retrieved by the Shuttle
Decay	12 Nov 1994
Technical data

Specifications


 Program: Spot

Satellite Pour l'Observation de la Terre

French remote sensing program decided in 1978 by the French government after a refusal of the ESA. Belgium and Sweden participated. Data is commercialized by a private company: Spot Image. Applications include geological, petroleum and mining research, cartography, agricultural forcasting and survey of natural disasters.

Geological mission: detection of geochemical and structural anomalies through stereo imagery useful for oil and mineral exploration

Agricultural mission: crop yield forecasting, flood damage analysis, etc.

Cartographical mission: 1:50000 maps (1:25000 possible in some cases)

Planning mission: land use monitoring e.g. urban/rural boundary

Main Earth stations: Toulouse, France; Kiruna, Sweden; Prince Albert and Gatinea, Canada; Ladkraban, Thailand; Hatoyama, Japan; Islamabad, Pakistan; Hyderabad, India; Maspalamas, Spain and Ryad, Saudi Arabia.


Program: Spot

Spot 1

Spot 2

Spot 3


Spot 1, 2 & 3's specifications

Prime contractor	Matra Marconi Space
Platform	Spot
Mass at launch	1900 kg
Payload mass	790 kg
Dimension	2 x 2 x 3.5 m
Solar array	8 m span
Stabilization	3 axis
DC power	1100 W
Design lifetime	3 years
Telemetry/data	X-band (20 W)


Spot 1, 2 & 3's payload

2 HRV (High Resolution Visible) detectors - linear array CCD detectors using push-broom scanning

Wavebands	Panchromatic (PAN): 0.51-0.73 µm (visible, near IR) Multispectral (XS): 0.50-0.59 µm (green) 0.61-0.68 µm (red) 0.79-0.89 µm (near IR)
Swath width	60 km (each HRV)
Resolution	Panchromatic: 10 m Multispectral: 20 m

HRVs are steerable to either side of the ground track (+/- 27°) to provide re-visits and stereoscopic images


 Spot 1

General

Designation	16613 / 86019A
Launch date	22 Feb 1986
Country of origin	France
Mission	Remote sensing
Perigee/Apogee	821/823 km
Inclination	98.7°
Period	101.3 min
Orbital cycle	26 days
Launch vehicle	Ariane V16
Technical data

Specifications

Payload


 Spot 2

General

Designation	20436 / 90005A
Launch date	22 Jan 1990
Country of origin	France
Mission	Remote sensing
Perigee/Apogee	821/823 km, same plan as Spot 1 but at its antipode
Inclination	98.7°
Period	101.3 min
Launch vehicle	Ariane V35
Technical data

Specifications

Payload

Beacon frequency: 8.307 GHz. Data: 8.253 GHz; output rate: 2 x 25 Mbit/s


 Spot 3

General

Designation	22823 / 93061A
Launch date	26 Sep 1993
Country of origin	France
Mission	Remote sensing
Perigee/Apogee	821/823 km
Inclination	98.7°
Period	101.3 min
Launch vehicle	Ariane V59

Cost: $250 million ($125 million for launch)

Technical data

Specifications

Payload


 Spot 4

General

Designation
Launch date	planned in 1997
Country of origin	France
Mission	Remote sensing
Perigee/Apogee	832 km
Inclination	98.7°
Period	101 min
Orbital cycle	3.7, 26 days
Launch vehicle	Ariane
Launch site
Technical data

Specifications

Prime contractor	Matra Marconi Space
Platform	Spot MkII
Mass at launch	2550 kg
Payload mass	1350 kg
Dimension	2 x 2 x 5.35 m
Stabilization	3 axis
DC power	EOL: 2200 W
Design lifetime	3 years
Telemetry/data	S-band: 2205.930 MHz X-band: 8253.000 MHz
2 HRVIR (High Resolution Visible IR) detectors

Wavebands	0.50-0.59 µm (green) 0.61-0.68 µm (red) 0.79-0.89 µm (near IR) 1.53-1.75 µm (mid-IR)
Swath width	60 km (each HRV)
Resolution	Monospectral: 10 m Multispectral: 20 m

HRVs are steerable to either side of the ground track (+/- 27°) to provide re-visits and stereoscopic images

Vegetation monitoring Instrument; Optical laser data relay to Artemis satellite (PASTEL)


 Program: Sputnik

Soviet experimental program


Program: Sputnik

Sputnik 01

Sputnik 02

Sputnik 03

Sputnik 04

Sputnik 05

Sputnik 06

Sputnik 07

Sputnik 09

Sputnik 10


 Sputnik 01

General

Designation	00002 / 57001B
Launch date	4 Oct 1957
Country of origin	CIS
Mission	Scientific: ionosphere study
Perigee/Apogee	227/945 km
Inclination	65°
Period	96.1 min
Launch vehicle	Semiorka (R7)
Launch site	Tyuratam
Mass at launch	83.6 kg

First satellite ever launched

Sphere made of aluminum of 58 cm diameter with 4 antennas. Its 2 radio transmitters send signals during 21 days. It enabled propagation and ionospherical studies.

End of life

Decay	3 Jan 1958


 Sputnik 02

General

Designation	00003 / 57002A
Launch date	3 Nov 1957
Country of origin	CIS
Mission	Scientific: Sun observation
Perigee/Apogee	212/1660 km
Inclination	65.3°
Period	103.7 min
Launch vehicle
Launch site	Tyuratam
Mass at launch	508.3 kg

1.2 m high cone that carried Laika (a dog) the first living creature in Space. Also studied X-rays and UV radiations from the Sun. The dog died after a few days.

End of life

Decay	14 Apr 1958


 Sputnik 03

General

Designation	00008 / 58004B
Launch date	15 May 1958
Country of origin	CIS
Mission	Scientific: ionosphere study
Perigee/Apogee	217/1.864 km
Inclination	65.2°
Period	106 min
Launch vehicle
Launch site	Tyuratam
Mass at launch	1327 kg (payload: 970 kg)
End of life

Decay	6 Apr 1960


 Sputnik 04

General

Designation	00034 / 60005A
Launch date	15 May 1960
Country of origin	CIS
Mission
Perigee/Apogee	284/514 km
Inclination	65°
Period	92.5 min
Launch vehicle
Launch site	Tyuratam
End of life

Decay	5 Sep 1962


 Sputnik 05

General

Designation	00055 / 60011A
Launch date	19 Aug 1960
Country of origin	CIS
Mission
Perigee/Apogee	281/340 km
Inclination	64.6°
Period	90.7 min
Launch vehicle
Launch site	Tyuratam
End of life

Decay	20 Aug 1960


 Sputnik 06

General

Designation	00065 / 60017A
Launch date	1 Dec 1960
Country of origin	CIS
Mission
Perigee/Apogee	123/269 km
Inclination	65°
Period	88.4 min
Launch vehicle
Launch site	Tyuratam
End of life

Decay	2 Dec 1960


 Sputnik 07

General

Designation	00071 / 61002A
Launch date	4 Feb 1961
Country of origin	CIS
Mission
Perigee/Apogee	212/318 km
Inclination	64.9°
Period	89.8 min
Launch vehicle
Launch site	Tyuratam
End of life

Decay	26 Feb 1960


 Sputnik 09

General

Designation	00091 / 61008A
Launch date	9 Mar 1961
Country of origin	CIS
Mission
Perigee/Apogee	173/239 km
Inclination	64.9°
Period	88.6 min
Launch vehicle
Launch site	Tyuratam

Vostok 1 repetition

End of life

Decay	9 Mar 1961


 Sputnik 10

General

Designation	00095 / 61009A
Launch date	25 Mar 1961
Country of origin	CIS
Mission
Perigee/Apogee	175/175 km
Inclination	64.9°
Period	88.6 min
Launch vehicle
Launch site	Tyuratam

Vostok 1 repetition

End of life

Decay	25 Mar 1961


 Program: Sret

Satellite de Recherche et d'Etudes Technologiques

French experimentation program


Program: Sret

Sret 1

Sret 2


 Sret 1

General

Designation	05928 / 72025B
Launch date	4 Apr 1972
Country of origin	France
Mission	Technology experimentation
Perigee/Apogee	480/39248 km
Inclination	65.6°
Period	735 min
Launch vehicle
Launch site	Plesetsk
Mass at launch	15 kg

Technological satellite to test solar cell

End of life

Decay	26 Feb 1974


 Sret 2

General

Designation	07910 / 75049B
Launch date	6 Jun 1975
Country of origin	France
Mission	Technology experimentation
Perigee/Apogee	513/40825 km
Inclination	62.8°
Period	737.8 min
Launch vehicle
Launch site	Plesetsk
Mass at launch	30 kg

Tested a passive cryogenic radiative system


 Program: Sross

Streach ROhini Sat Services

Indian experimental program


Program: Sross

Sross 1

Sross 2

Sross 3

Sross C2


 Sross 1

General

Launch date	24 Mar 1987
Country of origin	India
Mission
Launch vehicle	ASLV #1
End of life

Out of service	24 Mar 1987
Cause	launch failure


 Sross 2

General

Launch date	12 Jul 1988
Country of origin	India
Mission
Launch vehicle	ASLV #2
End of life

Out of service	12 Jul 1988
Cause	launch failure


 Sross 3

General

Designation	21968 / 92028A
Launch date	20 May 1992
Country of origin	India
Mission
Perigee/Apogee	251/436 km
Inclination	46°
Period	91.4 min
Launch vehicle	ASLV #3
End of life

Decay	14 Jul 1992


 Sross C2

General

Designation	23099 / 94027A
Launch date	4 May 1994
Country of origin	India
Mission	Scientific: ionosphere study
Perigee/Apogee	430/619 km
Inclination	46°
Period	95.1 min
Launch vehicle	ASLV #4
Mass at launch	113 kg

It carried a Retarding Potential Analyzer (RPA) for measuring ionospheric plasma, and a Gamma ray detector.

Beacon freq.: 137.400 Mhz

It operates only on command so data reception is limited to sites close to India.


SSTP
 Program: SSTP

Space Spacecraft Technology Program

planned for 1995, 230 kg, remote sensing


 Starlette

Satellite de Taille Adaptée avec Réflecteur Laser pour l'ETude de la TErre

General

Designation	07646 / 75010A
Launch date	6 Feb 1975
Country of origin	France
Mission	Scientific: geodesy
Operator	CNES
Perigee/Apogee	805/1108 km
Inclination	49.8°
Period	104.2 min
Launch vehicle	Diamant #10
Mass at launch	47 kg

Sphere of 24 cm of uranium covered with reflectors. Measured the continental drift.


 Start 1

General

Designation	22561 / 93014A
Launch date	25 Mar 1993
Country of origin	CIS
Mission	Test
Perigee/Apogee	680/968 km
Inclination	75.8°
Period	101.4 min
Launch vehicle	Start #1


 Program: Statsionar

Soviet denomination for geostationary slots reservation used by Raduga and Gorizont satellites.

The "Express" denomination is used for the Express program.


Program: Statsionar

Statsionar-01, 75°E Statsionar-02, 35°E Statsionar-03, 85°E Statsionar-04, 14°W Statsionar-05, 53°E Statsionar-06, 90°E Statsionar-07, 140°E Statsionar-08, 25°W Statsionar-09, 45°E Statsionar-10, 170°W	Statsionar-11, 11°W Statsionar-12, 40°E Statsionar-13, 80°E Statsionar-14, 96.5°E Statsionar-15, 127°E Statsionar-16, 145°E Statsionar-17, 26.5°W Statsionar-18, 8°E Statsionar-19, 23°E Statsionar-20, 70°E	Statsionar-21, 103°E Statsionar-22, 1°E Statsionar-23, 15°E Statsionar-24, 49°E Statsionar-25, 37.5°W Statsionar-26, 155°W Statsionar-27, 12°E


 Statsionar-01

Location: 75°E

Begin	End	Satellite
22 Dec 1975		Raduga 01


 Statsionar-02

Location: 35°E

Begin	End	Satellite
11 Sep 1976		Raduga 02
23 Jul 1977		Raduga 03
18 Jul 1978		Raduga 04
20 Feb 1980		Raduga 06
18 Mar 1981		Raduga 08
9 Oct 1981		Raduga 10
26 Nov 1982		Raduga 11
15 Feb 1984		Raduga 14
15 Nov 1985		Raduga 17
20 Oct 1988	?	Raduga 22
19 Dec 1991		Raduga 28


 Statsionar-03

Location: 85°E

Begin	End	Satellite
25 Apr 1979		Raduga 05
8 Apr 1983		Raduga 12
19 Mar 1987		Raduga 20
20 Dec 1990	< Feb 1995	Raduga 26
30 Sep 1993		Raduga 30


Statsionar-04
 Statsionar-04 / Loutch-02 / Express-02

Location: 14°W

Begin	End	Satellite
14 Jun 1980		Gorizont 04
30 Mar 1988		Gorizont 15
20 Jun 1990		Gorizont 20
13 Oct 1994		Express 01


Statsionar-05
 Statsionar-05 / Express-05

Location: 53°E

Begin	End	Satellite
19 Dec 1978		Gorizont 01
6 Jul 1979		Gorizont 02
28 Dec 1979		Gorizont 03
22 Apr 1984		Gorizont 09
18 Jan 1985		Gorizont 11
26 Jan 1989	? moved	Gorizont 17
22 Nov 1992		Gorizont 27


Statsionar-06
 Statsionar-06 / Loutch-03 / Express-07

Location: 90°E

Begin	End	Satellite
30 Nov 1983		Gorizont 08
18 Nov 1986		Gorizont 13
3 Nov 1990		Gorizont 21
28 Oct 1993		Gorizont 28


Statsionar-07
 Statsionar-07 / Loutch-04 / Express-10

Location: 140°E

Begin	End	Satellite
11 May 1987		Gorizont 14
6 Jul 1989		Gorizont 18


 Statsionar-08

Location: 25°W

Begin	End	Satellite
5 Oct 1980		Raduga 07
17 Jan 1986		Raduga 18
14 Apr 1989	Jul 1995	Raduga 23


 Statsionar-09

Location: 45°E

Begin	End	Satellite
25 Aug 1983		Raduga 13
8 Aug 1985		Raduga 16
15 Dec 1989	?	Raduga 24
18 Feb 1994	Jul 1995	Raduga 31
Sep 1995		Raduga 23


 Statsionar-10

Location: 170°W

Begin	End	Satellite
20 Oct 1982		Gorizont 06
25 Oct 1986		Raduga 19
?		Raduga 21


Statsionar-11
 Statsionar-11 / Loutch-06 / Express-03

Location: 11°W

Begin	End	Satellite
30 Jun 1983		Gorizont 07
15 Jul 1992		Gorizont 26


Statsionar-12
 Statsionar-12 / Loutch-07 / Express-04

Location: 40°E

Begin	End	Satellite
10 Jun 1986		Gorizont 12
23 Nov 1990		Gorizont 22
Feb 1996		Gorizont 31


Statsionar-13
 Statsionar-13 / Loutch-08 / Express-06

Location: 80°E

Begin	End	Satellite
1 Aug 1984		Gorizont 10
18 Aug 1988		Gorizont 16
23 Oct 1991		Gorizont 24


Statsionar-14
 Statsionar-14 / Loutch-09 / Express-08

Location: 96.5°E

Begin	End	Satellite
15 Mar 1982		Gorizont 05
28 Sep 1989		Gorizont 19
Mar 1996		Gorizont 22


 Statsionar-15

Location: 128°E

Begin	End	Satellite
22 Jun 1984		Raduga 15
10 Dec 1987	? moved	Raduga 21
28 Feb 1991		Raduga 27


Statsionar-16
 Statsionar-16 / Loutch-10 / Express-11

Location: 145°E

Begin	End	Satellite
		Gorizont 21


 Statsionar-17

Location: 26.5°W

Begin	End	Satellite


 Statsionar-18

Location: 8°E

Begin	End	Satellite


 Statsionar-19

Location: 23°E

Begin	End	Satellite


 Statsionar-20

Location: 70°E

Begin	End	Satellite
21 Jun 1989		Raduga 1-1
15 Feb 1990		Raduga 25
28 Dec 1994		Raduga 32


Statsionar-21
 Statsionar-21 / Loutch-05 / Express-09

Location: 103°E

Begin	End	Satellite
2 Jul 1991		Gorizont 23
2 Apr 1992		Gorizont 25


 Statsionar-22

Location: 1°E

Begin	End	Satellite


 Statsionar-23

Location: 15°E

Begin	End	Satellite


 Statsionar-24

Location: 49°E

Begin	End	Satellite
22 Jun 1989	?	Raduga 24
27 Dec 1990		Raduga 1-2
5 Feb 1994		Raduga 1-3


Statsionar-25
 Statsionar-25 / Express-01

Location: 37.5°W

Begin	End	Satellite


Statsionar-26
 Statsionar-26 / Express-12

Location: 155°W

Begin	End	Satellite


 Statsionar-27

Location: 12°E

Begin	End	Satellite
?		Raduga 22
25 Mar 1993		Raduga 29


 Stella

General

Designation	22824 / 93061B
Launch date	26 Sep 1993
Country of origin	France
Mission	Scientific: geodesy
Perigee/Apogee	793/803 km
Inclination	98.7°
Period	100.8 min
Launch vehicle	Ariane V59
Technical data

Specifications

Prime contractor	CNES
Platform
Mass at launch	48 kg
Mass in orbit
Diameter	24 cm (sphere)
Stabilization
DC power
Design lifetime

Its a sphere of 24 cm diameter with 20 sides and 60 laser reflectors. As Starlette or Lageos 2 Stella is designed to be tracked by laser (1 cm accuracy) by ground stations all around the world (in France: le Cergue in Grasse). It is made of impoverish uranium for the maximum stability. Will enable to make a map of the globe.


 Program: Step

Space Test Experiment Platform

American small satellite program to test technology, operated by the USAF Phillips Lab


Program: Step

Step 0

Step 1

Step 2

Step 3

Step 4


 Step 1

Also called P90 A

General

Launch date	27 Jun 1994
Country of origin	United States
Mission	Military: technology
Launch vehicle	Pegasus #6 (XL)
End of life

Out of service	27 Jun 1994
Cause	Destroyed on launch with the launcher

Operated by USAF and built by TRW from an Eagle platform

It carried radio propagation experiments, a plasma environment analyser, the CHAMPION ionosphere-magnetosphere coupling experiment, and an accelerometer and mass spectrometer to study the upper atmosphere.


 Step 2

Also called P91 A

General

Designation	23105 / 94029A
Launch date	19 May 1994
Country of origin	United States
Mission	Military: technology
Perigee/Apogee	604/818 km
Inclination	81.9°
Period	99 min
Launch vehicle	Pegasus #5

Operated by USAF and built by TRW from a lightstar Eagle platform. It will study propagation of radio signals through the ionosphere; carries SIDEX, a signal indentification experiment.


 Step 3

General

Launch date	22 Jun 1995
Country of origin	United States
Mission	Military: technology
Launch vehicle	Pegasus #9 (XL)
Mass at launch	265 kg
End of life

Out of service	22 Jun 1995
Cause	Launch failure

Built by TRW, it carried the SAMME (Space Active Modular Materials Experiments) payload to study exposure to space of solar cells and advanced materials, as well as vibration suppression technology and experimental computer disk drives.


 Step 4

General

Designation
Launch date	planned in 1997
Country of origin	United States
Mission	Military: technology
Perigee/Apogee
Inclination
Period
Launch vehicle	Pegasus
Launch site	Vandenberg


 Program: STRV

Space Technology Research Vehicle

English experimental program operated by DRA (Defence Research Agency), the new name for the RAE (Royal Aircraft Establishment). RAE was the lead agency for all of Britain's technology

(as opposed to science or communications) satellites.

Designed to test spacecraft systems and technologies in orbit and investigate the effect of high radiation doses, atomic oxygen erosion and spacecraft charging.


Program: STRV

STRV 1A

STRV 1B


STRV's specifications

Prime contractor	DRA (Defense Research Agency) Aerospace Division
Mass at launch	~ 50 kg
Dimension	0.45 x 0.45 x 0.47 m
Stabilization	Spin stabilized
DC power	BOL: 27 W EOL: 24 W
Design lifetime	1 year


STRV's Payload

Several instruments to measure radiation dose, particle fluxes, electrostatic charging, etc.

Telemetry data rate	1 kbps
Transmitter power	0.5 W, 2 W
Frequencies	Uplink: 2.025-2.12 GHz Downlink: 2.2-2.3 GHz


 STRV 1A

General

Designation	23125 / 94034B
Launch date	17 Jun 1994
Country of origin	United Kingdom
Mission	Military: technology
Perigee/Apogee	251/35518 km
Inclination	7.3°
Period	627 min
Launch vehicle	Ariane V64
Mass at launch	50 kg

Carries experiments to study surface erosion effects on spacecraft materials, a cosmic ray detector, and a gamma ray burst experiment. Will test new solar cells and measure static charge on its surfaces.

Technical data

Specifications

Payload

Spin rate: 10 rpm


 STRV 1B

General

Designation	23126 / 94034C
Launch date	17 Jun 1994
Country of origin	United Kingdom
Mission	Military: technology
Perigee/Apogee	239/35588 km
Inclination	7.3°
Period	628 min
Launch vehicle	Ariane V64
Mass at launch	53 kg

Carries an experimental cooler, solar cells, and electronics.

Technical data

Specifications

Payload

Spin rate: 5 rpm


 Sunsat

General

Designation
Launch date	planned in Jan 1996
Country of origin	South Africa
Mission	Telecommunication, HAM
Perigee/Apogee
Inclination
Period
Launch vehicle
Launch site

Designed and built by engineering students at the Electronic Systems Laboratory at Stellenbosch University. In exchange for a US National Aeronautics and Space Administration launch, Sunsat will carry a precision GPS receiver and a set of Laser retro-reflectors, for NASA's use.

The payload includes duplicate transmitters and receivers for the 2-meter and 70-cm bands, a 24-cm (1260 Mhz) receiver and 13-cm (2400-MHz) receiver. A number of uplink and downlink frequency combinations are possible. Sunsat will offer extensive digital communication capability. One of the 2-meter receivers has four IF sections connected to 1200-baud AFSK packet modems. The satellite carries three G3RUH-compatible 9600-baud modems that can be switched to various receivers and transmitters.


 Program: Superbird

Japanese telecommunication program operated by the Space Communications Corporation (SCC)

Contact

Fax: +81-3-5462-1390


Program: Superbird

Superbird A1

Superbird A2

Superbird B1

Superbird C

Superbird D


Superbird's specifications

Prime contractor	Ford Aerospace / Space Systems/Loral
Platform	FS 1300
Mass at launch	2492 kg
Mass in orbit	1505 kg
Dimension	2.41 x 2.58 x 2.2 m
Solar array	20.3 m span
Stabilization	3 axis
DC power	4460 W
Design lifetime	10 years


Superbird's X-band

Main transponders	2
Backup transponders
Power	40 W (TWTA)
Bandwidth	40 MHz
Coverage
EIRP	37 dBW
Polarization


Superbird's Ku-band

Main transponders	19
Backup transponders
Power	35 W (TWTA)
Bandwidth	36 MHz
Coverage
EIRP	53 dBW
Polarization


Superbird's Ka-band

Main transponders	3 (spot beam)+7
Backup transponders
Power	29 W (TWTA)
Bandwidth	100 MHz
Coverage
EIRP	spot beam: 59 dBW others: 55 dBW
Polarization


 Superbird A1

General

Designation	20040 / 89041A
Launch date	5 Jun 1989
Country of origin	Japan
Mission	Telecommunications
Geostationary orbit	life time in 158°E
Launch vehicle	Ariane V31
End of life

Out of service	Dec 1990
Cause	Propellant leak
Technical data

Specifications

X-band

Ku-band

Ka-band


 Superbird D

End of life

Out of service	22 Feb 1990
Cause	Launch failure: Ariane V36
Technical data

Specifications

X-band

Ku-band

Ka-band


 Superbird B1

General

Designation	21893 / 92010A
Launch date	26 Feb 1992
Country of origin	Japan
Mission	Telecommunications
Geostationary orbit	162°E
Launch vehicle	Ariane V49
Technical data

Specifications

X-band

Ku-band

Ka-band

Ku-band EIRP coverage (dBW)


Superbird B1's Ku-band EIRP


 Superbird A2

General

Designation	22253 / 92084A
Launch date	1 Dec 1992
Country of origin	Japan
Mission	Telecommunications
Geostationary orbit	158°E
Launch vehicle	Ariane V55
Technical data

Specifications

X-band

Ku-band

Ka-band


 Superbird C

General

Designation
Launch date	planned in Jul 1997
Country of origin	Japan
Mission	Telecommunications
Geostationary orbit	144°E
Launch vehicle	Atlas 2AS
Launch site	Cape Canaveral

Satellite based on an HS-601 platform. 24 active transponders to carry television signals and business-communications services throughout Japan, Southern and Eastern Asia and Hawaii.

In addition to two conventional antennas the spacecraft will also feature a steerable spot beam designed and built by Mitsubishi to increase service where needed.

Investment is evaluated to $416 million including insurance


 Surfsat 1

Summer Undergraduate Research Fellowship SATellite

General

Designation	23711 / 95060B
Launch date	4 Nov 1995
Country of origin	Canada
Mission	Scientific
Perigee/Apogee	934/1494 km
Inclination	100.6°
Period	109 min
Launch vehicle	Delta 2 #229
Mass at launch	55 kg

Surfsat is bolted to Delta's second stage. It has its own solar cells and is not electricaly dependent of Delta.

Surfsat will be used as a test vehicle for NASA, supporting deep space communications research and training of tracking station personnel at NASA's Deep Space Network. The Deep Space Network transponders will operate in Ka-band at 32 GHz (atmospheric studies). The VLBI transponders (X- and Ku-band) will enable testing of ground equipment for VSOP (Japan) and Radioastron (Russian project).

Designed by Caltech undergraduates with the help of JPL.


 Program: Symphonie

French and German telecommunication program. The French Saros project and the German Olympia project merged with the help of a cooperation signed on 22 Jan 1963 and 16 Jun 1967. The satellites were built by CIFAS, a consortium gathering Aérospatiale, Thomson CSF, SAT and MBB, Siemens and AEG Telefunken.

The program enabled the use of the SAMSON (Station à Antenne Miniature pour Service Occasionnel Numérique) portable station: transportable in 2 containers containing telecommunication equipments and a 4.8 m diameter antenna.


Program: Symphonie

Symphonie 1

Symphonie 2


Symphonie's specifications

Prime contractor	CIFAS
Platform
Mass at launch	400 kg
Mass in orbit	235 kg
Diameter	1.7 m
Height	0.5 m
Solar array	6.8 m span
Stabilization	3 axis (first civilian satellites 3 axis stabilized)
DC power	BOL: 300 W EOL: 180 W
Design lifetime	5 years
Capacity	600 phone circuits or 2 TV channels


Symphonie's C-band

Main transponders	2
Backup transponders
Power
Bandwidth	90 MHz
Coverage
EIRP	30 dBW
Polarization


 Symphonie 1

General

Designation	07578 / 74101A
Launch date	19 Dec 1974
Country of origin	Germany and France
Mission	Telecommunications
Geostationary orbit	see below
Launch vehicle	Thor Delta #106
Launch site	Cape Canaveral
Location

Begin	End	Position
L: 19 Dec 1974	1977	11.5°W
1977	Aug 1979	Indian ocean (for India)
Aug 1979	19 Feb 1983	Atlantic ocean
End of life

Out of service	19 Feb 1983
Technical data

Specifications

C-band


 Symphonie 2

General

Designation	08132 / 75077A
Launch date	27 Aug 1975
Country of origin	Germany and France
Mission	Telecommunications
Geostationary orbit	26°W
Launch vehicle	Thor Delta #114
Launch site	Cape Canaveral
End of life

Out of service	yes
Technical data

Specifications

C-band


 Program: Syncom

SYNchronous COMmunication

First american geostationary program. Satellites built by Hughes Aircraft


Program: Syncom

Syncom 1

Syncom 2

Syncom 3


Syncom's specifications

Prime contractor
Platform
Mass in orbit	40 kg
Length
Width
Height
Stabilization	Spin?
DC power
Design lifetime


Syncom's transmission payload

Main transponders	2
Backup transponders
Power	2 W
Bandwidth	300 phone circuits
Coverage
EIRP
Frequencies	upload: 7.4 GHz download: 1.8 GHz


 Syncom 1

General

Designation	00553 / 63004A
Launch date	14 Feb 1963
Country of origin	United States
Mission	Telecommunications
Geostationary orbit
Launch vehicle	Thor Delta #16
Launch site	Cape Canaveral
End of life

Out of service	14 Feb 1963
Cause	Lost on the way to geostationary orbit
Technical data

Specifications

Transmission payload


 Syncom 2

General

Designation	00634 / 63031A
Launch date	26 Jul 1963
Country of origin	United States
Mission	Telecommunications
Geostationary orbit	35797/35785 km, 33° inclined, above Brazil
Launch vehicle	Thor Delta #20
Launch site	Cape Canaveral

On 31 Oct 1963 the president of the radiocommunications conference in Geneva, Mr Gunnar Pedersen, inaugurated a telephone link to UN's center in New York by Syncom 2.

End of life

Out of service	yes
Technical data

Specifications

Transmission payload


 Syncom 3

General

Designation	00858 / 64047A
Launch date	19 Aug 1964
Country of origin	United States
Mission	Telecommunications
Geostationary orbit
Launch vehicle	Thor Delta #25
Launch site	Cape Canaveral

First geostationary satellite. Used to broadcast Tokyo's Olympic Games to the US in October 1964 and then for military links to Vietnam.

End of life

Out of service	yes
Technical data

Specifications

Transmission payload


 Taiyo

Means "sun", also called SRATS (Solar Radiation And Thermospheric Structure)

General

Designation	07671 / 75014A
Launch date	24 Feb 1975
Country of origin	Japan
Mission	Scientific: ionosphere and Sun study
Perigee/Apogee	250/2800 km
Inclination	33°
Period	116 min
Launch vehicle	Mu 3C
Launch site	Kagoshima
Mass at launch	86 kg
End of life

Decay	29 Jun 1980


 Program: Tansei

Means "blue light necklace"

Japanese program


Program: Tansei

Tansei 1

Tansei 2

Tansei 3

Tansei 4


 Tansei 1

Also called Tansei MRT

General

Designation	04952 / 71011A
Launch date	16 Feb 1971
Country of origin	Japan
Mission
Perigee/Apogee	986/1106 km
Inclination	29.7°
Period	106.1 min
Launch vehicle	Mu 4S
Launch site	Kagoshima
Mass at launch	63 kg


 Tansei 2

General

Designation	07122 / 74008A
Launch date	16 Feb 1974
Country of origin	Japan
Mission
Perigee/Apogee	284/3231 km
Inclination	31.2°
Period	121.7 min
Launch vehicle	Mu 3C
Launch site	Kagoshima
Mass at launch	56 kg
End of life

Decay	22 Jan 1983


 Tansei 3

General

Designation	09841 / 77012A
Launch date	19 Feb 1977
Country of origin	Japan
Mission
Perigee/Apogee	796/3804 km
Inclination	65.8°
Period	134.1 min
Launch vehicle	Mu 3H
Launch site	Kagoshima
Mass at launch	134 kg


 Tansei 4

General

Designation	11706 / 80015A
Launch date	17 Feb 1980
Country of origin	Japan
Mission
Perigee/Apogee	517/608 km
Inclination	38.7°
Period	95.9 min
Launch vehicle	Mu 3S1
Launch site	Kagoshima
Mass at launch	185 kg
End of life

Decay	12 May 1983


 TD 1A

Thor Delta 1A

General

Designation	05879 / 72014A
Launch date	12 Mar 1972
Country of origin	Europe
Mission	Scientific: UV astronomy
Perigee/Apogee	523/550 km
Inclination	97.6°
Period	95.4 min
Launch vehicle	Thor Delta #88
Launch site	Vandenberg
Mass at launch	472 kg
End of life

Decay	9 Jan 1980


 Program: TDF

Télédiffusion De France

French direct TV program operated by TDF. Designed to promote the D2MAC TV standard

Contact

TDF

21-27 rue Barbès, 92120 Montrouge, France

Tel: +33-1-4965-1000

Fax: +33-1-4657-4850


Program: TDF

TDF 1

TDF 2


TDF's specifications

Prime contractor	Eurosatellite/Aerospatiale
Platform	Spacebus 300
Mass at launch	2100 kg
Mass in orbit	1300 kg
Payload mass	206 kg: transponders: 114 kg, antennas: 92 kg
Dimension	2.4 x 1.65 x 6.4 m
Solar array	19.3 m span
Stabilization	3 axis
DC power	BOL: 4500 W EOL: equinox: 3642 W, solstice: 3311 W
Payload power	2455 W
Design lifetime	7 years


TDF's Ku-band

Main transponders	5
Backup transponders	1
Power	230 W
Bandwidth	27 MHz
Coverage and EIRP	1 beam centered on France: 63 dBW
Polarization	RHCP
Frequencies	Uplink: 17.3-17.7 GHz Donwlink: 11.7-12.1 GHz
Video excursion	13.5 MHz/v


TDF's EIRP


 TDF 1

General

Designation	19621 / 88098A
Launch date	28 Oct 1988
Country of origin	France
Mission	Direct TV
Geostationary orbit	18.9°W
Launch vehicle	Ariane V26
Technical data

Specifications

Ku-band

EIRP coverage (dBW)

Transponder 1 was destroyed by propellant leaks.


 TDF 2

General

Designation	20705 / 90063A
Launch date	24 Jul 1990
Country of origin	France
Mission	Direct TV
Geostationary orbit	18.9°W
Launch vehicle	Ariane V37
Technical data

Specifications

Ku-band

EIRP coverage (dBW)


 Program: TDRS

Tracking and Data Relay Satellite

American telecommunication program operated by NASA. Provides communications, tracking, telemetry, data acquisition and command services essential to Shuttle and low-Earth orbital spacecraft missions. The TDRS system can provide communications services to orbital spacecraft over 85 percent of each orbit for most satellites, and continuous service for some orbital positions.

Control center is in White Sands, New Mexico.

The TDRS system was initiated following studies in the early 1970s which showed that a system of telecommunications satellites, operated from a single ground station, could meet the needs of NASA's mission better and more cost-effectively than the then existing network of tracking and communications ground stations located around the world.

In addition to the Shuttle, TDRS customers include GRO, UARS, HST, ERBS, EUVE, Topex Poseidon and other military missions.

Contact

Columbia Communications Corp.

888 17th Street NW, 12th floor, Washington DC 20006, USA

Tel: +1-202-429-9033

Fax: +1-202-296-2962


Program: TDRS

TDRS 1

TDRS 2

TDRS 3

TDRS 4

TDRS 5

TDRS 6

TDRS 7

TDRS 8-10 (or H-J)


TDRS 1 to 7's specifications

Prime contractor	Contel & NASA
Platform	TRW Space and Communications
Mass at launch	approx. 2200 kg
Mass in orbit	2120 kg
Dimension	Hexagonal shape
Stabilization	3 axis
DC power	BOL: 2000 W EOL: 1700 W
Design lifetime	10 years

Each satellite has 5 antenna systems: 2 for single access, multiple access, STGL and S-band omni for satellite control.

For SA service, each TDRS has two dual-feed S-band, Ku-band parabolic antennas. These antennas are free to be positioned in two axes, directing the radio beam to orbiting user spacecraft below. These antennas are used primarily to relay communications to and from user spacecraft. The high data rate provided by these antennas is available to users on a time-shared basis. Each antenna is capable of supporting two-user spacecraft services simultaneously -one at S-band and one at Ku-band- provided both users are within the beam width of the antenna.

The MA antenna array, consisting of 30 elements, is hard-mounted on the spacecraft body on the surface of the antenna module facing the Earth.

Another antenna, a 2-meter parabolic reflector, provides the prime link for relaying transmissions to and from the ground terminal at Ku-band.


TDRS's S-band

Main transponders	2+8
Backup transponders	2+4
Power	(2+2) transponders of 26 W (8+4) transponders of 3.5 W
Bandwidth
Coverage
EIRP
Polarization


TDRS's C-band

Main transponders	12
Backup transponders
Power	5 W
Bandwidth	36 MHz
Coverage
EIRP	32 dBW
Polarization


TDRS's Ku-band

Main transponders	4+2
Backup transponders	2+2
Power	(4+2) transponders of 25 W (2+2) transponders of 1.5 W?
Bandwidth	50 & 225 MHz
Coverage
EIRP	50 dBW
Polarization


 TDRS 1

General

Designation	13969 / 83026B
Launch date	4 Apr 1983
Country of origin	United States
Mission	Telecommunications
Geostationary orbit	see below
Launch vehicle	STS 06

Its propulsion device (IUS) didn't work. The satellite reached the geostationary orbit by himself, using much of his propellant.

Still partially operational, it is though to provide communication services with the South Pole.

Location

Begin	End	Position
L: 4 Apr 1983		GTO
17 Oct 1983		41°W
1989		79°W
Feb 1995	May 1995	85°E, inclined
Jul 1995	mid-Dec 1995	139°W, inclined
?		49°W, inclined (to support ELVs over the South Atlantic)
Technical data

Specifications

S-band

C-band

Ku-band


 TDRS 2

General

Launch date	28 Jan 1986
Country of origin	United States
Mission	Telecommunications
Geostationary orbit	n/a
Launch vehicle	STS 33
End of life

Out of service	28 Jan 1986
Cause	Exploded with Challenger
Technical data

Specifications

S-band

C-band

Ku-band


 TDRS 3

General

Designation	19548 / 88091B
Launch date	29 Sep 1988
Country of origin	United States
Mission	Telecommunications
Geostationary	see below
Launch vehicle	STS 26R

Still partially operational

Location

Begin	End	Position
L: 29 Sep 1988	Apr 1995	171°W
Jun 1995		85°E, inclined: supports GRO and tested with HST
Technical data

Specifications

S-band

C-band

Ku-band


 TDRS 4

General

Designation	19883 / 89021B
Launch date	13 Mar 1989
Country of origin	United States
Mission	Telecommunications
Geostationary orbit	41°W
Launch vehicle	STS 29
Technical data

Specifications

S-band

C-band

Ku-band

EIRP coverage in C-band

Ku-band downlink:13.750-15.115 GHz. Beacon: 2.211 GHz


TDRS 4's C-band EIRP


 TDRS 5

General

Designation	21639 / 91054B
Launch date	2 Aug 1991
Country of origin	United States
Mission	Telecommunications
Geostationary orbit	174°W
Launch vehicle	STS 43
Technical data

Specifications

S-band

C-band

Ku-band


 TDRS 6

Also called TDRS F

General

Designation	22314 / 93003B
Launch date	13 Jan 1993
Country of origin	United States
Mission	Telecommunications
Geostationary orbit	46°W, in reserve
Launch vehicle	STS 54
Technical data

Specifications

S-band

C-band

Ku-band


 TDRS 7

Also called TDRS G

General

Designation	23613 / 95035A
Launch date	13 Jul 1995 at 19:55 UT
Country of origin	United States
Mission	Telecommunications
Geostationary orbit	171°W, in reserve
Launch vehicle	STS 70 + IUS

Tested in 150°W slot

The IUS consists of two Solid Rocket Motors (SRM's) which inject the TDRS/IUS into geostationary orbit. The IUS SRM 1 first place the TDRS/IUS into a transfer orbit with an apogee near geosynchronous altitude (burn at 20:55 UT). At the first apogee the IUS SRM 2 fired to place the TDRS/IUS in geostationary orbit (14 Jul at 02:30 UT). The TDRS/IUS was then maneuvered to the appropriate orientation and TDRS 7 separated from the IUS.

Technical data

Specifications

S-band

C-band

Ku-band


TDRS 8
 TDRS 8, 9 & 10

Or TDRS HIJ

Those 3 satellites will be built by Hughes and made from an modified HS-601 platform NASA required to be reimbursed for failures!

It will add Ka-band to the existing S- and Ku-band, with potential data rates as high as 650Mb/s.

Planned for 1999


 TELE X

General

Designation	19919 / 89027A
Launch date	2 Apr 1989
Country of origin	Sweden
Mission	Direct TV
Geostationary orbit	5°E
Launch vehicle	Ariane V30

NSAB is owned 50% by Teracom Svensk Rundradio and 50% by Swedish Space Corporation.

Contact

NSAB (Nordiska Satellitaktiebolaget) c/o Teracom Svensk Rundradio

Box 17666, S-11892 STOCKHOLM, Sweden

Tel: + 46 8 671 20 00

Fax: +46 8 671 20 01

Technical data

EIRP coverage (dBW)

Specifications

Prime contractor	Eurosatellite & Aérospatiale
Platform	Spacebus 300
Mass at launch	2089 kg
Payload mass	170 kg
Dimension	2.4 x 1.65 x 2.4 m
Solar array	19 m span
Stabilization	3 axis
DC power	BOL: 3200 W
Payload power	2000 W
Design lifetime	7 years
Ku-band

Main transponders	4
Backup transponders	2
Power	230 W (TWTA)
Bandwidth	(2+1) transponders of 27 MHz (2+1) transponders of 40 & 86 MHz
Coverage and EIRP	Scandinavia: 61 dBW
Polarization	LHCP
Frequencies	Uplink: 17.7-18.1 GHz Downlink: 12.1-12.65 GHz


TELE X's EIRP


 Program: Telecom

French program decided on 20 Feb 1979 operated by France Telecom (designed by the CNES).

Mission: telecommunication to over-sea territories, military communications and TV and data transmission.

Contact

France Telecom

103 rue de Grenelle, 75007 Paris, France

Tel: +33-1-4444-4522

Fax: +33-1-4555-9072


Program: Telecom

Telecom 1A

Telecom 1B

Telecom 1C

Telecom 2A

Telecom 2B

Telecom 2C

Telecom 2D


Telecom 1's specifications

Prime contractor	Matra Marconi Espace
Platform	ECS
Mass at launch	1210 kg
Mass in orbit	653 kg
Payload mass	134.4 kg: transponders: 107 kg, antennas: 27.4 kg
Dimension	2.06 x 1.9 x 2.2 m
Solar array	16 m span
Stabilization	3 axis
DC power	EOL: equinox: 1483 W, solstice: 1450 W
Payload power	717.3 W
Design lifetime	7 years

Telemetry is transmitted in S-band in backup mode and in C-band in normal mode.


Telecom 1's C-band

Main transponders	4
Backup transponders	2
Power	8.5 W (TWTA)
Bandwidth	1 transponder of 36 MHz 3 transponder of 120 MHz
Coverage & EIRP	Hemispheric: 29.5 dBW Spot: to West Indies and Guyana (transponder #2): 35 dBW
Polarization	LHCP
Transponder frequency chart (GHz)

RHCP Uplink	Transponder	LHCP Downlink
5.945	C1	3.720
6.040	C2	3.775
6.135	C3	3.910
6.360	C4	4.135


Telecom 1's X-band (7.3 and 8 GHz)

Main transponders	2
Power	20 W (TWTA)
Bandwidth	40 MHz
Coverage	Atlantic and Indian ocean
EIRP	31.3 dBW

Syracuse is the communication system used on the transponders


Telecom 1's Ku-band

Main transponders	6
Backup transponders	3
Power	20 W (TWTA)
Bandwidth	36 MHz
Coverage	Europe
EIRP	49 dBW
Polarization	linear V
Transponder frequency chart (GHz)

Horizontal Uplink	Transponder	Vertical Downlink
14.022	K1	12.522
14.064	K2	12.564
14.106	K3	12.606
14.148	K4	12.648
14.190	K5	12.690
14.232	K6	12.732


Telecom 2's specifications

Prime contractor	Matra Marconi Espace
Platform	Eurostar 2000
Mass at launch	2225 kg
Mass in orbit	1005 kg
Payload mass	407.4 kg: transponders: 307.4 kg, antennas: 100 kg
Dimension	2 x 2.1 x 2 m
Solar array	22 m span
Stabilization	3 axis
DC power	BOL: 3850 W EOL: equinox: 3397 W, solstice: 3143 W (nickel hydrogen 86 A/H batteries)
Payload power	2549 W
Design lifetime	10 years


Telecom 2's C-band

Main transponders	10
Backup transponders	4
Power	11.5 W
Bandwidth	4 transponders of 90 MHz 6 transponders of 50 MHz
Coverage (uplink)	Global
Coverage (downlink)	Spot: France, St Pierre & Miquelon, West Indies and Guyana Semi global: Reunion
EIRP	Spot: 39 dBW Semi global: 32.5 dBW
Polarization	circular R/L
Uplink	5.925-6.425 GHz
Transponder frequency chart (GHz)

LHCP Downlink	Transponder	RHCP Downlink
	C1A	3.710
	C1B	3.738
	C2A	3.768
	C2B	3.795
3.849	C3
3.907	C4
3.965	C5
4.019	C6
4.154	C7


Telecom 2's X-band

Main transponders	4+2
Backup transponders	2+1
Power	(2+1) transponders of 40 W (TWTA) (4+2) transponders of 20 W (TWTA)
Bandwidth	3 transponders of 40 MHz 1 transponder of 60 MHz 1 transponder of 80 MHz
Coverage	global: center Europe & mobile
EIRP	31.3 dBW
Access	MRF (Multiple à Répartition en Fréquence) or MRC (Multiple à Répartition par Code)
Uplink	7.9-8.395 GHz
Downlink	7.25-7.745 GHz


Telecom 2's Ku-band

Main transponders	11
Backup transponders	4
Power	55 W (TWTA)
Bandwidth	36 MHz
Coverage and EIRP	Europe: 52.5 dBW
Polarization	linear H/V
Uplink	14.0-14.25 GHz
Transponder frequency chart (GHz)

Horizontal Downlink	Transponder	Vertical Downlink
	K1	12.522
12.543	K7
	K2	12.564
12.585	K8
	K3	12.606
12.627	K9
	K4	12.648
12.669	K10
	K5	12.690
12.711	K11
	K6	12.732


Telecom 2's EIRP (Ku-band)


 Telecom 1A

General

Designation	15159 / 84081B
Launch date	4 Aug 1984
Country of origin	France
Mission	Telecommunications
Geostationary orbit	8°W
Launch vehicle	Ariane V10

Had insulation failures that caused the communication system Syracuse problems

End of life

Out of service	Apr 1992?
Technical data

Specifications

C-band

X-band

Ku-band

Apogee kick motor: Mage 2


 Telecom 1B

General

Designation	15678 / 85035B
Launch date	8 May 1985
Country of origin	France
Mission	Telecommunications
Geostationary orbit	5°W
Launch vehicle	Ariane V13
End of life

Out of service	15 Jan 1988
Cause	Stabilization power supply failure
Technical data

Specifications

C-band

X-band

Ku-band


 Telecom 1C

General

Designation	18952 / 88018B
Launch date	11 Mar 1988
Country of origin	France
Mission	Telecommunications
Geostationary orbit	see below
Launch vehicle	Ariane V21
Location

Begin	End	Position
L: 11 Mar 1988		5°W
Aug 1992		3°E (inclined since fall 1995)
Technical data

Specifications

C-band

X-band

Ku-band


 Telecom 2A

General

Designation	21813 / 91084A
Launch date	16 Dec 1991
Country of origin	France
Mission	Telecommunications
Geostationary orbit	see below
Launch vehicle	Ariane V48
Location

Begin	End	Position
L: 16 Dec 1991	Apr 1992 (tests)	3°E
Apr 1992		8°W

Test from Mulhouse in Ku-band, Pleumeur Bodou in C-band and from Southern France in X-band. It entered service for the Olympic Games and then it was re-tested in eclipse period. Finaly it was positioned in 8°W

Technical data

Specifications

C-band

X-band

Ku-band

Beacon: 3.816 GHz RHCP

EIRP coverage (dBW)

C-band

Ku-band

Ku-band

Bandwidth	32 MHz
Video excursion	22 MHz/v
Mono bandwidth	310 KHz
Mono de-emphasis	50 µs
Stereo bandwidth	130 KHz
Stereo de-emphasis	75 µs
Stereo expansion	Panda 1


Telecom 2A's C-band EIRP


 Telecom 2B

General

Designation	21939 / 92021A
Launch date	15 Apr 1992
Country of origin	France
Mission	Telecommunications
Geostationary orbit	5°W
Launch vehicle	Ariane V50

Entered in service on 22 Jul 1992

Technical data

Specifications

C-band

X-band

Ku-band

Beacon: 3.815 GHz RHCP (or 3737.500 MHz?)

EIRP coverage (dBW)

C-band

Ku-band

Ku-band

Bandwidth	32 MHz
Video excursion	22 MHz/v
Mono bandwidth	180 KHz
Mono de-emphasis	J17
Mono expansion	Alcatel
Stereo bandwidth	130 KHz
Stereo de-emphasis	J17
Stereo expansion	Alcatel


Telecom 2's C-band EIRP


 Telecom 2C

General

Designation	23730 / 95067A
Launch date	6 Dec 1995
Country of origin	France
Mission	Telecommunications
Geostationary orbit	3°E
Launch vehicle	Ariane V81

Tested at 1°E

Technical data

Specifications

C-band

X-band

Ku-band

The spacecraft has an R-4D-12 liquid apogee engine. The mass of Telecom 2C is 1120 kg, with a fuel load of 1163 kg giving a launch mass of 2283 kg.

EIRP coverage (dBW)

C-band

Ku-band


 Telecom 2D

General

Designation
Launch date	1998
Country of origin	France
Mission	Telecommunications
Geostationary orbit
Launch vehicle	Ariane

S-band beacon: 2207.130 MHz


 Program: Telstar

American telecommunication program operated by AT&T

Contact

AT&T Skynet Satellite Services

#900 Routes 202/206, Room 2A-115V, Bedminster, NJ 07921-0752, USA

Tel: 800-847-9335

Fax: +1-908-234-7940


Program: Telstar

Telstar 1

Telstar 2

Telstar 301

Telstar 302

Telstar 303

Telstar 401

Telstar 402

Telstar 402R

Telstar 5

Telstar 6

Telstar 7

Telstar 8


Telstar 1 & 2's specifications

Prime contractor
Platform
Mass at launch	80 kg
Mass in orbit
Diameter	86 cm
Height
Stabilization	Spin?
DC power
Design lifetime


Telstar 1 & 2's C-band

Main transponders	1
Backup transponders
Power	2 W
Bandwidth	600 phone circuits
Coverage
EIRP
Polarization


Telstar 3's specifications

Prime contractor	Hughes
Platform	HS-376
Mass at launch	3423 kg (with PAM-D)
Mass in orbit	625 kg
Diameter	2.16 m
Height	6.8 m deployed
Stabilization	Spin stabilized
DC power	BOL: 800 W
Design lifetime	10 years


Telstar 3's C-band

Main transponders	24
Backup transponders
Power	8.5 W (TWTA)
Bandwidth	36 MHz
Coverage and EIRP	CONUS: 34 dBW
Polarization	linear H/V


Telstar 4's specifications

Prime contractor	GE Astro Space
Platform	GE 7000
Mass at launch	3331 kg
Mass in orbit
Dimension	4.08 x 2.22 x 2.54 m
Solar array	24.5 m span
Stabilization	3 axis
DC power	BOL: 6400 W EOL: 5000 W
Design lifetime	12 years

Cross-strapping possible in both directions


Telstar 4's C-band

Main transponders	24
Backup transponders	4
Power	variable 11-21 W
Bandwidth	36 MHz
Coverage
EIRP	38 dBW
Polarization	linear H/V


Telstar 4's Ku-band

Main transponders	16 to 24 (variable)
Backup transponders	12
Power	60 W standard, up to 120 W (TWTA)
Bandwidth	54 MHz & 27 MHz
Coverage
EIRP	50 dBW
Polarization

8 transponders can be splited in 16 transponders of 27 MHz. The 120 W transponders are achieved by using the backup transponders


Telstar 4's Ku-band frequency chart
 Telstar 4's Ku-band frequency plan (GHz)

Horizontal Uplink	Horizontal Downlink	Transponder	Vertical Downlink	Vertical Uplink	Notes
14.030		1	11.730
	11.743	2		14.043
14.090		3	11.790
	11.803	4		14.103
14.150		5	11.850		120 W capable
	11.863	6		14.163	120 W capable
14.210		7	11.910		120 W capable
	11.923	8		14.223	120 W capable
14.271		9 (A/B)	11.971		full or A: 120 W capable
	11.984	10 (A/B)		14.284	full or A: 120 W capable
14.333		11 (A/B)	12.033		full or A: 120 W capable
	12.046	12 (A/B)		14.346	full or A: 120 W capable
14.395		13 (A/B)	12.095		full or A: 120 W capable
	12.108	14 (A/B)		14.408	full or A: 120 W capable
14.457		15 (A/B)	12.157		full or A: 120 W capable
	12.170	16 (A/B)		14.470	full or A: 120 W capable


Telstar 30x's EIRP


Telstar 4's C-band EIRP


Telstar 4's Ku-band EIRP


 Telstar 1

General

Designation	00340 / 62029A
Launch date	10 Jul 1962
Country of origin	United States
Mission	Telecommunications
Perigee/Apogee	942/5646 km
Inclination	44.8°
Period	157.8 min
Launch vehicle	Thor Delta #11
Launch site	Cape Canaveral

First live broadcasts between the United States and Europe. At the end of 1962, after 4 months, a transistor of the system failed. AT&T managed to repair it! First satellite equipped with transponders and thus amplification: thus first active satellite.

End of life

Out of service	21 Feb 1963
Technical data

Specifications

C-band


 Telstar 2

General

Designation	00573 / 63013A
Launch date	7 May 1963
Country of origin	United States
Mission	Telecommunications
Perigee/Apogee	966/10807 km
Inclination	42.8°
Period	225.3 min
Launch vehicle	Thor Delta #18
Launch site	Cape Canaveral
Mass at launch	79.5 kg
End of life

Out of service	May 1965
Technical data

Specifications

C-band


 Telstar 301

General

Designation	14234 / 83077A
Launch date	28 Jul 1983
Country of origin	United States
Mission	Telecommunications
Geostationary orbit	see below
Launch vehicle	Thor Delta #171
Launch site	Cape Canaveral
Location

Begin	End	Position
L: 28 Jul 1983		96°W
Mar 1994	Aug 1994	107.3°W (Anik E2 replacement)
Jan 1995	...	see Arabsat 1E
Technical data

EIRP coverage (dBW)

Specifications

C-band

Transponder frequency chart


 Telstar 302

General

Designation	15237 / 84093D
Launch date	1 Sep 1984
Country of origin	United States
Mission	Telecommunications
Geostationary orbit	85°W, inclined
Launch vehicle	STS 16
Technical data

EIRP coverage (dBW)

Specifications

C-band

Transponder frequency chart


 Telstar 303

General

Designation	15826 / 85048D
Launch date	19 Jun 1985
Country of origin	United States
Mission	Telecommunications
Geostationary orbit	see below
Launch vehicle	STS 25
Location

Begin	End	Position
L: 19 Jun 1985		125°W
< May 1992		123°W, inclined
Technical data

EIRP coverage (dBW)

Specifications

C-band

Transponder frequency chart


 Telstar 401

General

Designation	22927 / 93077A
Launch date	16 Dec 1993
Country of origin	United States
Mission	Telecommunications
Geostationary orbit	97°W
Launch vehicle	Atlas Centaur

Entered service on 1 Feb 1994

Technical data

Specifications

C-band

Ku-band

Transponder frequency chart

Ku-band Transponder frequency chart

EIRP coverage (dBW)

C-band

Ku-band


 Telstar 402

General

Designation	23249 / 94058A
Launch date	9 Sep 1994
Country of origin	United States
Mission	Telecommunications
Geostationary orbit	was expected in slot 89°W
Launch vehicle	Ariane V67

Cost: $200 million

End of life

Out of service	9 Sep 1994
Cause	Explosion after pressurisation

The second of two pyrovalve firings to enable its propulsion system set off an explosion and a disastrous leak.

Technical data

Specifications

C-band

Ku-band

Transponder frequency chart

Ku-band Transponder frequency chart

EIRP coverage (dBW)

C-band

Ku-band


 Telstar 402R

General

Designation	23670 / 95049A
Launch date	Sep 1995
Country of origin	United States
Mission	Telecommunications
Geostationary orbit	89°W
Launch vehicle	Ariane V78

Started serving on 1st December 1995

Technical data

Specifications

C-band

Ku-band

C-band Transponder frequency chart

Ku-band Transponder frequency chart

EIRP coverage (dBW)

C-band

Ku-band


 Telstar 5

General

Designation
Launch date	planned in mid-1997
Country of origin	United States
Mission	Telecommunications
Geostationary orbit	93°W
Launch vehicle

substitutes to Telstar 403

Technical data

Design lifetime: 15 years

C-band

Main transponders	24
Backup transponders
Power	16 W
Bandwidth	36 MHz
Coverage	US (50 states) + Caribbean
EIRP	CONUS: 37 dBW Alaska: 32 dBW Hawaii: 36 dBW Puerto Rico/US Virgin Islands: 33 dBW
Polarization	linear H/V
Ku-band

Main transponders	24+4
Backup transponders
Power	100 W
Bandwidth	24 transponders of 27 MHz 4 transponders of 54 MHz
Coverage	US (50 states) + Caribbean, Mexico and Southern Canada
EIRP	CONUS: 46.5 dBW Alaska: 42 dBW Hawaii: 45.5 dBW Puerto Rico/US Virgin Islands: 44.7 dBW Mexico: 43.5 dBW Southern Canada: 44.5 dBW
Polarization	linear H/V

Ku-band: No variable power nor cross-strapping like on the 40x series


 Telstar 6

Planned in 1999 for 129° W slot

Designed with 28 100-Watt Ku-band transponders (4 are 54 MHz and 24 are 27 MHz) and 24 16-Watt C-band transponders.

Ku-band: No variable power nor cross-strapping like on the 40x series

Aimed to Alaska and to replace Aurora 2


 Telstar 7

Planned in 2000 for 83° W slot

Designed with 28 100-Watt Ku-band transponders (4 are 54 MHz and 24 are 27 MHz) and 24 16-Watt C-band transponders.

Ku-band: No variable power nor cross-strapping like on the 40x series


 Telstar 8

Should be a ground backup for satellites of the 5 to 7 series, same design


 Temisat

Telespazio Micro Satellite

General

Designation	22783 / 93055B
Launch date	31 Aug 1993 at 04:40 UT, released at 15:20 UT from Meteor 2-21
Country of origin	Italy
Operator	Telespazio
Mission	Telecommunications
Perigee/Apogee	932/967 km
Inclination	82.5°
Period	104 min
Launch vehicle	Cyclone
Launch site	Plesetsk

Will relay environmental data from field sites

Technical data

Specifications

Prime contractor	Kayser-Threde
Mass at launch	30 or 42 kg
Dimension	0.35 x 0.35 x 0.35 m
Stabilization	3 axis (magnetotorquer)
Design lifetime	5 years
Payload

Frequency	148-150 MHz 137-138 MHz
Uplink	10 channels (9 simultaneously) 1200 baud
Downlink	6 channels (3 simultaneously) 2 x 4800 baud + 1200 baud


 Program: Tempo

DBS satellite program operated by TCI

2 satellites planned

Aimed at direct TV broadcasting to the territory of the continental part of the United States, to Alaska, Hawaii and Puerto Rico

Contact

Tempo Satellite Inc.

4100 East Dry Creek Road, Littleton, CO 80122, USA

Tel: +1-303-486-3800

Fax: +1-303-486-3891


 Tempo 1

General

Designation
Launch date	planned in Jun 1996
Country of origin	United States
Mission	Telecommunications
Geostationary orbit	148 or 110°W depending on auction
Launch vehicle	Proton
Technical data

Specifications

Prime contractor	Space Systems/Loral
Platform	FS 1300
Mass at launch
Mass in orbit
Dimension
Solar array
Stabilization
DC power
Design lifetime	10 years
Ku-band

Main transponders	32
Backup transponders
Power	107 W (TWTA)
Bandwidth	24 MHz
Coverage	CONUS+
EIRP
Polarization

Can be operated as 16 transponders of 214 W each


 Program: Thaicom

Thai telecommunication program operated by Shinawatra, a national operator which has secured a 30-year concession

Contact

Shinawatra Satellite Company Ltd

41/103 Rattanathibet Road, Nonthaburi, 11000, Thailand

Tel: +662-591-0736

Fax: +662-591-0706


Program: Thaicom

Thaicom 1

Thaicom 2

Thaicom 3


Thaicom 1 & 2's specifications

Prime contractor	Hughes
Platform	HS-376
Mass at launch	1080 kg
Mass in orbit	629 kg
Diameter	2.16 m
Height	6.6 m deployed
Stabilization	Spin stabilized
DC power	BOL: 700 W
Design lifetime	10 years
Apogee motor	Thiokol Star 30


Thaicom 1 & 2's C-band

Main transponders	10
Backup transponders	2
Power	11 W
Bandwidth	36 MHz
Coverage and EIRP	South Eastern Asia: 37 dBW A spot covers central Europe
Polarization	linear


Thaicom 1 & 2's Ku-band

Main transponders	2
Backup transponders	1
Power	47 W (TWTA)
Bandwidth	54 MHz
Coverage and EIRP	Thailand: 50 dBW
Polarization	linear


Thaicom C-band's EIRP


Thaicom Ku-band's EIRP


 Thaicom 1

General

Designation	22931 / 93078B
Launch date	18 Dec 1993
Country of origin	Thailand
Mission	Telecommunications
Geostationary orbit	78.5°E
Launch vehicle	Ariane V62

First Thai satellite

Technical data

Specifications

C-band

Ku-band

Polarization: H

EIRP coverage (dBW)

C-band

Ku-band


 Thaicom 2

General

Designation	23314 / 94065B
Launch date	8 Oct 1994
Country of origin	Thailand
Mission	Telecommunications
Geostationary orbit	78.5°E
Launch vehicle	Ariane V68
Technical data

Specifications

C-band

Ku-band

Polarization: V

EIRP coverage (dBW)

C-band

Ku-band


 Thaicom 3

General

Designation
Launch date	planned for 1996
Country of origin	Thailand
Mission	Telecommunications
Geostationary orbit	planned in 120°E (dispute with Apstar 1A)
Launch vehicle	Ariane
Launch site

Cost: $200 million

Thaicom 4 should be launched 6 months after Thaicom 3

Technical data

Specifications

Prime contractor	Aerospatiale
Platform
Mass at launch	2600/2700 kg
Mass in orbit
Length
Width
Height
Stabilization
DC power
Design lifetime

Steerable antennas

C-band

Main transponders	24
Backup transponders
Power
Bandwidth
Coverage & EIRP	Thailand: ? Vietnam to Western Europe: 34.5 dBW
Polarization
Ku-band

Main transponders	12
Backup transponders
Power
Bandwidth
Coverage
EIRP
Polarization


 Thor

General

Old name	BSB 2
Country	Norway
Mission	Direct TV
Geostationary orbit	0.8°W

Bought for $42 million

Operator: Norvegian Telecom

Contact

Tele TV AS

Storingst 4, 0158 Oslo, Norway

Tel: +47-2-415960

Fax: +47-2-415970

Technical data

Specifications

Ku-band

EIRP Coverage (dBW)


Thor's EIRP


 Thor 2A

General

Designation
Launch date	spring 1997
Country of origin
Operator	Telenor Satellite Services AS
Mission
Geostationary orbit
Launch vehicle	Delta 2
Launch site

To be delivered on orbit

Technical data

Specifications

Prime contractor	Hughes
Platform	HS-376HP (49th to be built)
Mass at launch
Mass in orbit
Dimension
Solar array	(gallium arsenide)
Stabilization	spin stabilized
DC power	1200 W
Design lifetime	11 years
Ku-band

Main transponders	15
Backup transponders
Power	40 W
Bandwidth
Coverage
EIRP
Polarization


 Program: Thurayya

Project of Etisalat, the United Arab Emirates (UAE) telecommunications firm (60% government-owned) to launch a one billion dollar satellite system to boost its mobile telephones network

The satellite system, named Thurayya, will provide services to UAE users of Two-way mobile telephones compatible with the Global System for Mobile communications (GSM). The system will make services available to remote sea and rural areas and will cover most Arab states, parts of the Indian subcontinent and Europe. No launch date set yet, no tendres released.

Etisalat said earlier it was considering another satellite for fixed communications units and television broadcasts.


 Program: Tiros

Television and Infra Red Observation Satellite

American meteorological program

In 1960, Tiros 1, the first true weather satellite, was launched. With each succeeding generation of satellites, remote sensing instruments became increasingly sophisticated and today's high quality pictures are a far cry from the first tentative trials.

TIROS was a simple hatbox-shaped craft carrying special television cameras that viewed Earth's cloud cover from a 450 mile orbit. The pictures radioed back to Earth provided meteorologists with a new tool - a nephanalysis, or cloud chart.

By 1965, nine more TIROS satellites were launched. They had progressively longer operational times, carried infrared radiometers to study Earth's heat distribution, and several were placed in polar orbits to increase picture coverage over the first TIROS in its near-equatorial orbit.

TIROS 8 had the first Automatic Picture Transmission (APT) equipment that allowed pictures to be sent back right after they were taken instead of having to be stored for later transmission. Eventually, APT pictures could be received on fairly simple ground stations anywhere in the world, even in high school classrooms.

TIROS 9 and 10 were test satellites of improved configurations for the Tiros Operational Satellite (TOS) system. Operational use started in 1966. In orbit, the TOS satellites were called ESSA. TOS satellites were placed in Sun-synchronous orbits, so they passed over the same position on Earth's surface at exactly the same time each day; this allowed meteorologists to view local cloud changes on a 24-hour basis.

Several ITOS (for Improved TOS satellites) have been launched since 1970 and are the workhorses of the meteorologists. In orbit they are called NOAA for the National Oceanographic and Atmospheric Administration which is responsible for their operation.


Program: Tiros

Tiros 01

Tiros 02

Tiros 03

Tiros 04

Tiros 05

Tiros 06

Tiros 07

Tiros 08

Tiros 09

Tiros 10

Tiros N


 Tiros 01

General

Designation	00029 / 60002B
Launch date	1 Apr 1960
Country of origin	United States
Mission	Meteorology
Perigee/Apogee	656/696 km
Inclination	48.4°
Period	98.3 min
Launch vehicle	Thor Able
Launch site	Cape Canaveral
Mass at launch	119.5 kg

Transmits the first pictures of the cloud cover


 Tiros 02

General

Designation	00063 / 60016A
Launch date	23 Nov 1960
Country of origin	United States
Mission	Meteorology
Perigee/Apogee	546/610 km
Inclination	48.5°
Period	96.2 min
Launch vehicle	Thor Delta #3
Launch site	Cape Canaveral


 Tiros 03

General

Designation	00162 / 61017A
Launch date	12 Jul 1961
Country of origin	United States
Mission	Meteorology
Perigee/Apogee	723/790 km
Inclination	47.9°
Period	100 min
Launch vehicle	Thor Delta #5
Launch site	Cape Canaveral


 Tiros 04

General

Designation	00226 / 62002A
Launch date	8 Feb 1962
Country of origin	United States
Mission	Meteorology
Perigee/Apogee	693/811 km
Inclination	48.3°
Period	99.9 min
Launch vehicle	Thor Delta #7
Launch site	Cape Canaveral


 Tiros 05

General

Designation	00309 / 62025A
Launch date	19 Jun 1962
Country of origin	United States
Mission	Meteorology
Perigee/Apogee	571/889 km
Inclination	58.1°
Period	99.4 min
Launch vehicle	Thor Delta #10
Launch site	Cape Canaveral


 Tiros 06

General

Designation	00397 / 62047A
Launch date	18 Sep 1962
Country of origin	United States
Mission	Meteorology
Perigee/Apogee	639/645 km
Inclination	58.3°
Period	97.6 min
Launch vehicle	Thor Delta #12
Launch site	Cape Canaveral


 Tiros 07

General

Designation	00604 / 63024A
Launch date	19 Jun 1963
Country of origin	United States
Mission	Meteorology
Perigee/Apogee	275/281 km
Inclination	58.2°
Period	90.1 min
Launch vehicle	Thor Delta #19
Launch site	Cape Canaveral
End of life

Decay	3 Jun 1994


 Tiros 08

General

Designation	00716 / 63054A
Launch date	21 Dec 1963
Country of origin	United States
Mission	Meteorology
Perigee/Apogee	669/703 km
Inclination	58.5°
Period	98.5 min
Launch vehicle	Thor Delta #22
Launch site	Cape Canaveral
Mass at launch	102.4 kg

The APT (Automatic Puncture Transmission) camera enabled, for the first time, small antennas to receive pictures.


 Tiros 09

General

Designation	00978 / 65004A
Launch date	22 Jan 1965
Country of origin	United States
Mission	Meteorology
Perigee/Apogee	702/2563 km
Inclination	96.4°
Period	118.9 min
Launch vehicle	Thor Delta #28
Launch site	Cape Canaveral

Test satellite for the Tiros Operational Satellite (TOS)


 Tiros 10

General

Designation	01430 / 65051A
Launch date	2 Jul 1965
Country of origin	United States
Mission	Meteorology
Perigee/Apogee	721/807 km
Inclination	98.8°
Period	100.1 min
Launch vehicle	Thor Delta #32
Launch site	Cape Canaveral

Test satellite for the Tiros Operational Satellite (TOS)


 Tiros N

General

Designation	11060 / 78096A
Launch date	13 Oct 1978
Country of origin	United States
Mission	Meteorology
Perigee/Apogee	829/845 km
Inclination	98.7°
Period	101.7 min
Launch vehicle	Atlas F
Launch site	Vandenberg

Was a research and development spacecraft serving as a protoflight for the operational follow-on series

Technical data

Specifications

Prime contractor	GE Astro Space
Platform	Tiros N
Mass at launch	~720 kg
Mass in orbit
Diameter	1.88 m
Heigth	3.71 m
Solar array	1 single panel
Stabilization
DC power
Design lifetime


 TOMS

Total Ozone Mapping Satellite

General

Designation
Launch date	planned in Jun 1996
Country of origin	United States
Mission	ozone study
Perigee/Apogee
Inclination
Period
Launch vehicle	Pegasus XL
Launch site
Mass at launch	295 kg
Contact

http://pao.gsfc.nasa.gov/gsfc/service/gallery/fact_sheets/earthsci/toms.htm


 Topex Poseidon

ocean TOPography EXperiment

General

Designation	22076 / 92052A
Launch date	10 Aug 1992
Country of origin	France and United States
Operator	NASA & CNES
Mission	Remote sensing
Perigee/Apogee	1330/1342 km
Inclination	66°
Period	112.4 min
Orbital cycle	10 days
Launch vehicle	Ariane V52

Mission: global ocean circulation, ocean currents, tides and surface topography

Cost: $480 million

The inclined orbit samples from 66 North to 66 South latitude: it allows the satellite to observe 90% of the ice-free oceans and all major straits. The orbit is not sun-synchronous and is prograde. The repeat-cycle is about 10 days, ie the satellite passes vertically over the same location in a 1-kilometer bandwidth every 10 days. It has been chosen to optimize the study of the temporal large scale oceanic variability. The distance between successive tracks is on the order of 310 km at the Equator. The local time of successive passes shifts by nearly two hours.

Technical data

Specifications

Prime contractor	Jet Propulsion Laboratory (+ bus: Fairchild, Poseidon: Alcatel Espace)
Platform	MultiMission Spacecraft bus
Mass at launch	2100 kg
DC power	1500 W
Stabilization	3 axis
Design lifetime	4 years
ALT (dual frequency radar altimeter) / NRA (NASA Radar Altimeter) (Topex)

Frequencies	5.3 GHz (C-band) 13.6 GHz (Ku-band)
Resolution	2-3 cm

NRA (206 Kg including redundance, 237 W) is the primary sensor for the TOPEX/POSEIDON mission. It has been provided by NASA. It is the fifth generation of altimeter (see Seasat and Geosat altimeters). The measurements made at the two frequencies are combined to obtain altimeter height of the satellite above the sea (altimeter range), the wind speed magnitude, the significant wave height and the ionospheric correction.

SSALT (Single-frequency Solid-state Radar Altimeter) (Poseidon)

Frequency	13.65 GHz (Ku-band)
Resolution	2-5 cm

SSALT (23 Kg without redundance, 49 W) validates the new technology of a low-power, light-weight altimeter for future Earth observing missions. It has been provided by the French Space Agency (CNES). It shares the same antenna as the NRA, thus only one altimeter operates at any given time. SSALT operates about 10% of the time that is one cycle in ten. The measurements give the same geophysical information as NRA's. However since this sensor uses a single frequency, an external correction for the ionosphere must be supplied (see the DORIS instrument).

TMR (Topex Microwave Radiometer)

Frequencies	18, 21 & 31 GHz

TMR (50 Kg including partial redundance, 25 W) measures the sea surface microwave brightness temperatures at three frequencies to provide the total vapor content in the troposphere along the altimeter beam. The 21 GHz channel is the primary channel for water vapor measurement. The 18 GHz channel is used to remove the effects of wind and the 37 GHz channel to remove cloud cover in the water vapor measurements. The measurements are combined to obtain the error in the satellite range measurements caused by pulse delay due to water vapor.

LRA (Laser Retroflector Array)

LRA (29 Kg) reflects laser signals from a network of 10 to 15 ground laser tracking stations to provide the baseline tracking data for precise orbit determination and to calibrate the altimeter bias.

DORIS (Doppler Orbitography and Radiopositioning Integrated by Satellite)

Frequencies	401.25 MHz 2036.25 MHz
Altitude accuracy	10 cm

DORIS (43 Kg including redundance, 21 W) is a French system that uses a two-channel receiver to observe the Doppler signals from a network of 40 to 50 ground transmitting beacons, spaced around the world. It provides all-weather global tracking of the satellite for precise orbit determination and an accurate correction for the influence of the ionosphere on both the Doppler signal and altimeter signals.

GPSDR (Global Positioning System Demonstration Receiver)

Frequencies	1227.6/1574.4 MHz

GPSDR (28 Kg without redundance, 29 W) uses a new GPS differential ranging technique for precise orbit determination. It receives signals from up to 6 GPS satellites. The GPS antenna is mounted on a long boom to reduce multipath effects which can severely corrupt the measurements. These data plus tracking of GPS from ground sites (3 minimum, 6 planned) allow nearly geometrical solutions.


 Tournesol

Also called D2A

General

Designation	05128 / 71030A
Launch date	15 Apr 1971
Country of origin	France
Mission	Scientific: Sun study and UV astronomy
Perigee/Apogee	457/696 km
Inclination	46.3°
Period	96.2 min
Launch vehicle	Diamant #7
Mass at launch	96 kg
End of life

Out of service	22 Jul 1973
Decay	28 Jan 1980


 Traac

General

Designation	00205 / 61031B
Launch date	15 Nov 1961
Country of origin	United States
Mission
Perigee/Apogee	955/1108 km
Inclination	32.4°
Period	105.8 min
Launch vehicle	Thor Ablestar
Launch site	Cape Canaveral
Mass at launch	90.4 kg

One of the 2 first satellites launched with the same vehicle (the other one is Transit 4B).


 Program: Transit

American navigation program

First navigation program launched in 1959 and operational in 1964. These satellites were for the U.S. Navy and in particular, the Fleet Ballistic Missle Submarines, to accurately verify their location. This program was superseded by NOVA and finally by the Global Positioning Satellites. It was commercialized in 1967.

First geodetic program to use the Doppler effect.

Technical data

Frequencies: 149.982 / 149.988 (operational channel) MHz and 399.9413 / 399.952 / 399.968 (operational channel) MHz


Program: Transit

Transit 2A

Transit 4A

Transit 4B

Transit 5BN1

Transit 5BN2


 Transit 2A

General

Designation	00045 / 60007A
Launch date	22 Jun 1960
Country of origin	United States
Mission	Navigation
Perigee/Apogee	604/988 km
Inclination	66.7°
Period	100.8 min
Launch vehicle	Thor Ablestar
Launch site	Cape Canaveral


 Transit 4A

General

Designation	00116 / 61015A
Launch date	29 Jun 1961
Country of origin	United States
Mission	Navigation
Perigee/Apogee	866/985 km
Inclination	66.8°
Period	103.5 min
Launch vehicle	Thor Ablestar
Launch site	Cape Canaveral
Mass at launch	79.1 kg

First satellite using a SNAP nuclear generator for power supply


 Transit 4B

General

Designation	00202 / 61031A
Launch date	15 Nov 1961
Country of origin	United States
Mission	Navigation
Perigee/Apogee	953/1104 km
Inclination	32.4°
Period	105.7 min
Launch vehicle	Thor Ablestar
Launch site	Cape Canaveral
Mass at launch	90.4 kg

Was launched with Traac: first time 2 satellites were launched with the same vehicle

Has a SNAP engine


 Transit 5BN1

General

Designation	00670 / 63038B
Launch date	28 Sep 1963
Country of origin	United States
Mission	Navigation
Perigee/Apogee	1062/1125 km
Inclination	90°
Period	107.1 min
Launch vehicle	Thor Ablestar
Launch site	Vandenberg


 Transit 5BN2

General

Designation	00704 / 63049B
Launch date	5 Dec 1963
Country of origin	United States
Mission	Navigation
Perigee/Apogee	1058/1109 km
Inclination	90.1°
Period	106.9 min
Launch vehicle	Thor Ablestar
Launch site	Vandenberg


 Program: Tsikada

Means cicada

Russian navigation program operational since April 1979 (deployment started in late-1976). The satellites composing this system based on the Tsikada bus. This bus carries the Tsikada navigation transponders and optional secondary payloads, e.g. RS, etc. The Cospas (Nadezhda) package is carried as this secondary payload on some satellites.

Lately the satellites are known as Nadezhda when they carry a Cospas receiver or part of Cosmos. A new generation is known as Kurs or Nadezhda M has just started and the satellites are in the Cosmos program (since it is still experimental). This generation is an new implementation of some equipment which can switch (on ground command) between two modes. The standard mode is Cospas for search and rescue. The other mode is the Kurs geolocation/data store-forward mode. The first use of this hardware was on Cosmos 2315. It was designed by Moscow's space instrumentation institute.

The system is based on 4 planes separated by 45° covering space in order to complete the Parus system.

Occupation of the planes

Plane 11	Plane 12	Plane 13	Plane 14
Cosmos 0883	Cosmos 0926	Cosmos 1000	Cosmos 1092
Cosmos 1168	Cosmos 1304	Cosmos 1226	Cosmos 1339
Cosmos 1383	Cosmos 1506	Cosmos 1447	Cosmos 1574
Cosmos 1553	Cosmos 1727	Cosmos 1655	Cosmos 1816
Cosmos 1791	Cosmos 1861	Cosmos 2123	Nadezhda 2
Nadezhda 1	Nadezhda 3	Tsikada 1	Nadezhda 4
Cosmos 2181
Cosmos 2230
Cosmos 2315
Note: Cosmos 1380 failed to replace Cosmos 1168 in 1982 (placed on a wrong orbit)

The satellites of this program are based on the Musson bus (see Parus for details).


Program: Tsikada

Tsikada 1


 Tsikada 1

General

Designation	23463 / 95002A
Launch date	24 Jan 1995 at 03:54 UT
Country of origin	CIS
Mission	Navigation
Perigee/Apogee	965/1020 km
Inclination	82.9°
Period
Launch vehicle	Cosmos 3M
Launch site	Plesetsk
Technical data

Downlink frequencies: 150 & 400 MHz

Plane 13


 TTS 1

Tethered Test Satellite, also called TSS (Tethered Satellite System)

General

Launch date	6 Aug 1992
Country of origin	Italy
Operator	CNR/PSN/NASA
Mission	Scientific
Launch vehicle	STS 46

To test power production (by induction). The satellite couldn't be deployed properly on STS 46 (only a few hundred meters).

Technical data

Specifications

Prime contractor	Aeritalia
Mass at launch	518 kg
Payload mass	66 kg
Diameter	1.6 m
Stabilization	Gravity gradient
DC power	180-200 W
Design lifetime	10 missions

Payload: instruments to measure electrodynamic properties of the ionosphere, magnetic fields and plasma

Tether (diameter: 2.54 mm) made from Kevlar sheated in Nomex with insulated copper-wire core


 TTS 2

Tethered Test Satellite, also called TSS 1R (Tethered Satellite System)

General

Designation	23805 / 96012B
Launch date	22 Feb 1996
Country of origin	Italy
Operator	CNR/PSN/NASA
Mission	Scientific
Launch vehicle	STS 75

The TSS project is a joint NASA/ASI (Italian Space Agency) effort. The 1.6 m diameter satellite is to be deployed on the end of a 20 kilometre long conductive tether to study the electrodynamic effects of moving such a tether through the Earth's magnetic field. The experiment will also test techniques for managing the tethered spacecraft at great distances. Second flight of the satellite which was worth about $200-400M (depending on whether or not you count the cost for the original satellite, modifications after the first flight, etc.)

The tether broke near full deployment (19 km) on 26 Feb at 01:30 UT. The initial orbit for the satellite was 316 x 413 km; meanwhile the shuttle wasat 291 x 299 km.

End of life

Decay	19 Mar 1996

Frequency downlink: 2260 MHz, uplink at 2081 MHz, 16 kbps data stream


 Program: Tubsat

Technische Universität Berlin SATellit

German small satellites program for data relay applications. 3-axis stabilized satellites


Program: Tubsat

Tubsat A

Tubsat B


 Tubsat A

General

Designation	21577 / 91050D
Launch date	17 Jul 1991
Country of origin	Germany
Mission	Scientific: animal migration studies for Berlin's university
Perigee/Apogee	762/772 km
Inclination	98.4°
Period	100.2 min
Launch vehicle	Ariane V44
Mass at launch	38 kg


 Tubsat B

General

Designation	22970 / 94003B
Launch date	25 Jan 1994
Country of origin	Germany
Mission	Technology
Perigee/Apogee	1183/1209 km
Inclination	82.55°
Period	109.35 min
Launch vehicle	Cyclone
Launch site	Plesetsk


 Program: Turksat

Turkish telecommunication program

Contact

General Directorate of PTT

Ruzgarli Sokak, Ankara 06101, Turkey

Tel: +90-312-366-1972

Fax: +90-312-311-7748


Program: Turksat

Turksat 1A

Turksat 1B

Turksat 1C

Turksat 1D


Turksat's specifications

Prime contractor	Aerospatiale
Platform	Spacebus 100B
Mass at launch	1775 kg
Mass in orbit	1078 kg
Dimension	2.8 x 2.2 x 2.5 m
Solar array	22.4 m span
Stabilization	3 axis
DC power	EOL equinox: 2900 W
Design lifetime	10 years
Apogee motor	MBB S400 (liquid fuel)


Turksat's Ku-band

Main transponders	16
Backup transponders	8
Power	55 W (TWTA)
Bandwidth	10 transponders of 36 MHz 6 transponders of 72 MHz
Coverage and EIRP	Turkey: 51 dBW Central Europe: 48 dBW Central Asia: 45 dBW
Polarization	linear H/V


Turksat 1B's EIRP (European & Turkish spots)


 Turksat 1A

End of life

Out of service	24 Jan 1994
Cause	Failure of Ariane V63
Technical data

Specifications

Ku-band


 Turksat 1B

General

Designation	23200 / 94049B
Launch date	10 Aug 1994
Country of origin	Turkey
Mission	Telecommunications
Geostationary orbit	42°E
Launch vehicle	Ariane V66

Cost: $300 million

Technical data

Specifications

Ku-band

EIRP coverage (dBW)

Transponder frequency chart (GHz)

Horizontal Downlink	Transponder	Vertical Downlink	Bandwidth (MHz)	Coverage
	4	10.970	36	Europe/Turkey
10.980	12		36	Turkey
	5	11.012	36	Europe/Turkey
11.030	13		36	Turkey
	6	11.054	36	Turkey
11.080	14		36	Turkey
	7	11.096	36	Turkey
11.130	15		36	Turkey
	8	11.162	72	Europe/Turkey
11.180	16		36	Turkey
11.486	9		72	Turkey
	1	11.490	72	Europe
11.574	10		72	Turkey
	2	11.590	72	Turkey/Asia
11.662	11		72	Turkey
	3	11.678	36	Turkey/Asia


 Turksat 1C

planned for launch in second half 1996, launched by Ariane

Should be the replica of Turksat 1A

Located at 31°E???


 Turksat 1D

Planned for 1999, Agreements have been signed with France's Aerospatiale


 Program: Tvsat

German direct TV program operated by the DBP (Deutsche BundesPost Telekom)


Program: Tvsat

Tvsat 1

Tvsat 2


Tvsat's specifications

Prime contractor	Eurosatellite and MBB
Platform	Spacebus 300
Mass at launch	2144 kg
Payload mass	195.9 kg: transponders: 97.6 kg, antennas: 98.3 kg
Dimension	2.4 x 1.64 x 6.4 m
Stabilization	3 axis
DC power	BOL: 4500 W EOL: equinox: 3312 W, solstice: 3060 W
Design lifetime	9 years


Tvsat's Ku-band

Main transponders	4
Backup transponders	2
Power	230 W (TWTA)
Bandwidth	27 MHz
Coverage	Europe
EIRP	65 dBW
Polarization	circular L
Frequencies	Uplink: 17.7-18.1 GHz Downlink: 11.7-12.5 GHz


 Tvsat 1

General

Designation	18570 / 87095A
Launch date	21 Nov 1987
Country of origin	Germany
Mission	Direct TV
Geostationary orbit	was expected in slot 19.2°W
Launch vehicle	Ariane V20

Not functional because a solar pannel remains in front of the antennas. In fact 2 bolts had been forgotten that screw the antenna tight for transportation before launch!

End of life

Out of service	February 1988
Technical data

Specifications

Ku-band


 Tvsat 2

General

Designation	20168 / 89062A
Launch date	8 Aug 1989
Country of origin	Germany
Mission	Direct TV
Geostationary orbit	see below
Launch vehicle	Ariane V33

Was available on 25 Aug 1989 to broadcast the Berlin's TV show. Was leased to Tele TV AS and co-located with Intelsat 702 in 1995

Location

Begin	End	Position
L: 8 Aug 1989	Feb 1995	19.2°W
Mar 1995		0.6°W
Technical data

Specifications

Ku-band

Video

Video excursion	13.5 MHz/v


 UARS

Upper Atmospheric Research Satellite

General

Designation	21701 / 91063B
Launch date	12 Sep 1991
Country of origin	United States
Mission	Scientific
Perigee/Apogee	555/586 km
Inclination	56.9°
Period	96 min
Launch vehicle	STS 48

Mission: systematic study of Earth's stratosphere, mesosphere and lower thermosphere with specialized payloads.

Cost: $630 million

Technical data

Specifications

Prime contractor	GE Astro
Platform	MultiMission Spacecraft bus
Mass at launch	6800 kg (2500 kg for the payload)
Diameter	5 m
Height	10 m
Solar array	1.5 x 3.3 m
Stabilization	3 axis
Design lifetime	3 years
CLAES (Cryogenic Limb Array Etalon Spectrometer)

Vertical profiles of minor species (between 10-60 km)

HALOE (Halogen Occultation Experiment)

Vertical distribution of minor species in stratosphere

ISAMS (Improved Stratospheric and Mesospheric Sounder)

Temperature and ozone concentrations in stratosphere and mesosphere

MLS (Microwave Limb Sounder)

ozone and other trace gases in stratosphere and mesosphere

HRDI (High Resolution Doppler Imager)

Horizontal windspeeds and temperature in upper troposhere and thermosphere

WINDII (Wind Imaging Interferometer)

Windspeed and temperature in mesosphere and lower thermosphere

PEM (Particule Environment Monitor)

Global input of charged particle energy

SOLSTICE (Solar Stellar Irradiance Comparison Experiment)

Full disk solar UV irradiance

SUSIM (Solar UV Spectral Irradiance Monitor)

solar irradiance, solar flux variability

ACRIM 2 (Active Cavity Radiometer Irradiance Monitor)

wide band total solar irradiance


Program: UHF
 Program: UHF Follow On

Also called for short UHF or UFO

US Navy telecommunication program composed of 10 satellites


Program: UHF

UHF 1

UHF 2

UHF 3

UHF 4

UHF 5

UHF 6

UHF 7

UHF 8


UHF's specifications

Prime contractor	Hughes
Platform	HS-601
Mass at launch	3000 kg (approx.)
Mass in orbit	1200 kg (approx.)
Length	3.2 m
Width	3.4 m
Height	3.4 m (7.0 m deployed)
Solar array	18.3 m span
Stabilization	3 axis
DC power
Design lifetime

Also downlinks in X-band?


UHF-band

Channels	39
Amplifiers	11
Power
Bandwidth	total: 555 KHz
Coverage
EIRP
Polarization

Within the 39 channels: 21 narrow band, 17 relay, and 1 Fleet Broadcast


EHF-band

Channels	11
Power
Bandwidth
Coverage & EIRP	global beam steerable 5° spot beam
Polarization

The EHF package provides enhanced anti-jam telemetry as well as command, broadcast andfleet interconnectivity communications.


 UHF 1

General

Designation	22563 / 93015A
Launch date	25 Mar 1993
Country of origin	United States
Mission	Military: telecommunications
Geostationary orbit	n/a
Launch vehicle	Atlas Centaur #074
End of life

Cause	was delivered in a wrong orbit due to a partial launch failure
Technical data

Specifications

UHF


 UHF 2

Also called USA 095

General

Designation	22787 / 93056A
Launch date	3 Sep 1993
Country of origin	United States
Mission	Military: telecommunications
Geostationary orbit	71.5°E, inclined
Launch vehicle	Atlas Centaur #79
Technical data

Specifications

UHF


 UHF 3

Also called USA 104

General

Designation	23132 / 94035A
Launch date	24 Jun 1994
Country of origin	United States
Mission	Military: telecommunications
Geostationary orbit	14.5°W, inclined
Launch vehicle	Atlas Centaur #83
Technical data

Specifications

UHF

Equipped with an ARC 490N (liquid fuel) apogee engine


 UHF 4

Also known as USA 108

General

Designation	23467 / 95003A
Launch date	29 Jan 1995
Country of origin	United States
Mission	Military: telecommunications
Geostationary orbit	178°W, inclined
Launch vehicle	Atlas Centaur #88

Tested in 170.5°W

Technical data

Specifications

UHF

EHF


 UHF 5

Also called USA 111

General

Designation	23589 / 95027A
Launch date	31 May 1995
Country of origin	United States
Mission	Military: telecommunications
Geostationary orbit	70.5°E, inclined
Launch vehicle	Atlas Centaur #92
Technical data

Specifications

UHF

EHF


 UHF 6

Also called USA 114

General

Designation	23696 / 95057A
Launch date	22 Oct 1995
Country of origin	United States
Mission	Military: telecommunications
Geostationary orbit	106°W
Launch vehicle	Atlas Centaur #95

Tested in 171.5°W and replaced Leasat 3

Technical data

Specifications

UHF

EHF


 UHF 7

General

Designation
Launch date	planned in 1996
Country of origin	United States
Mission	Military: telecommunications
Geostationary orbit
Launch vehicle	Atlas 2
Launch site	Cape Canaveral


 UHF 8, 9 & 10

will be launched in 1998

Will have the GBS (Global Broadcast System) modification. Each satellite would provide GBS service to one of these areas: Indian Ocean, Pacific Ocean and Atlantic Ocean.

The GBS payload will replace the current SHF capability with four 130 watt, 24 megahertz military Ka band transponders, 3 steerable downlink spot beam antennas and one steerable uplink (+ 1 fixed) receive antenna per satellite. The GBS augmentation would support a full range of simplex, or one-way communications, from national imagery dissemination to general news and entertainment broadcasts. Each satellite will provide 96 Mbps throughput


 Ume 1

Means "apricot tree flower", also called ISS 1

General

Designation	08709 / 76019A
Launch date	29 Feb 1976
Country of origin	Japan
Mission	Scientific: ionosphere study
Perigee/Apogee	985/1006 km
Inclination	69.7°
Period	105 min
Launch vehicle
Launch site	Tanegashima


 Ume 2

Also called ISS 2

General

Designation	10674 / 78018A
Launch date	16 Feb 1978
Country of origin	Japan
Mission	Scientifique
Perigee/Apogee	970/1219 km
Inclination	69.4°
Period	107.2 min
Launch vehicle
Launch site	Tanegashima


 Unamsat 1

General

Launch date	28 mar 1995
Country of origin	Mexico
Mission	Telecommunications
Launch vehicle	Start #2
End of life

Cause	Launcher failure
Decay	28 Mar 1995

Built by UNAM, the Autonomous University of Mexico.

Technical data

Frequency chart (MHz)

Downlink freq.	Transponder/Beacon	Mode
437.135	TX1	default
437.179	TX2
Uplink freq.	Transponder/Beacon	Mode
145.922	Channel A
145.942	Channel B
145.962	Channel C
145.872	Channel E/F


 Program: Uosat

University Of Surrey sATellite

Satellites built by Surrey's university in the UK

Contact

Professor Martin Sweeting

Managing Director

Surrey Satellite Technology Limited

Centre for Satellite Engineering Research University of Surrey Guildford

Surrey GU2 5XH United Kingdom

Tel: +44 1483 259143

Fax: +44-1483-259503

http://www.ee.surrey.ac.uk/EE/CSER/UOSAT/


Program: Uosat

Uosat 1

Uosat 2

Uosat 3

Uosat 4

Uosat 5


 Uosat 1

Also called UO-09 or Oscar 09

General

Designation	12888 / 81100B
Launch date	6 Oct 1981
Country of origin	United Kingdom
Mission	Telecommunications
Perigee/Apogee	372/374 km
Inclination	97.6°
Period	92 min
Launch vehicle	Thor Delta #157
Launch site	Vandenberg

Cost: $38000

First on-board computer (IHU - Integrated Housekeeping Unit) for battery and attitude management, remote control, and experiments.

End of life

Decay	13 Oct 1989
Technical data

Specifications

Prime contractor	University of Surrey (UK)
Platform	UoSAT
Mass at launch	52 kg
Dimension	0.74 x 0.42 x 0.42 m
Stabilization	3 axis (gravity gradient, magnetorquer)
DC power	BOL: 17 W EOL: 10 W
Design lifetime	3 years

Equipped with a vocal synthetisor and a TV camera.


 Uosat 2

Also called UO-11 or Oscar 11

General

Designation	14781 / 84021B
Launch date	1 Mar 1984
Country of origin	United Kingdom
Mission	Telecommunications
Perigee/Apogee	651/669 km
Inclination	97.8°
Period	98 min
Launch vehicle	Thor Delta #174
Launch site	Vandenberg

Function: Bulletin store and forward experiment, synthetic voice experiment, space dust and radiation experiments.

Technical data

Specifications

Prime contractor	University of Surrey (UK)
Platform	UoSAT
Mass at launch	60 kg
Dimension	0.58 x 0.36 x 0.36 m
Stabilization	3 axis (gravity gradient, magnetorquer)
DC power	BOL: 25 W (12 v, 6.4 Ah NiCd battery) EOL: 10 W
Design lifetime	3 years
Frequency chart

Downlink	1200 bps AFSK/FM (1200 and 2400 Hz tones), synthetic voice and CW. 145.826 MHz, 435.025 MHz, 2401.500 MHz


 Uosat 3

Also called UO-14 or Oscar 14

General

Designation	20437 / 90005B
Launch date	22 Jan 1990
Country of origin	United Kingdom
Mission	Telecommunications
Perigee/Apogee	781/797 km
Inclination	98.6°
Period	100.7 min
Launch vehicle	Ariane V35

Function: Packet Radio Mailbox and Digipeater

Since 1992 it is used by VITA (see also Gemstar)

Technical data

Specifications

Prime contractor	University of Surrey (UK)
Platform	UoSAT
Mass at launch	46 kg
Dimension	0.6 x 0.34 x 0.34 m
Stabilization	3 axis
DC power	EOL: 10 W
Design lifetime	3 years
Frequency chart

Uplink	9600 bps K9NG/G3RUH modulated FSK (FM) AX.25 145.975 MHz
Downlink	9600 bps K9NG/G3RUH modulated FSK (FM) AX.25 435.070 MHz
Beacon	1200 bps AFSK NBFM 435.070 MHz


 Uosat 4

Also called UO-15 or Oscar 15

General

Designation	20438 / 90005C
Launch date	22 Jan 1990
Country of origin	United Kingdom
Mission	Telecommunications
Perigee/Apogee	784/799 km
Inclination	98.6°
Period	100.7 min
Launch vehicle	Ariane V35
End of life

Out of service	23 Jan 1990
Cause	Failed
Technical data

Specifications

Prime contractor	University of Surrey (UK)
Platform	UoSAT
Mass at launch	46 kg
Dimension	0.6 x 0.34 x 0.34 m
Stabilization	3 axis
DC power	EOL: 10 W
Design lifetime	3 years


 Uosat 5

Also called UO-22 or Oscar 22

General

Designation	21575 / 91050B
Launch date	17 Jul 1991
Country of origin	United Kingdom
Mission	Telecommunications and Remote sensing
Perigee/Apogee	759/772 km
Inclination	98.4°
Period	100.2 min
Launch vehicle	Ariane V44

Function: Packet Radio Mailbox, Digipeater and a CCD camera experiment (EIS).

Technical data

Specifications

Prime contractor	University of Surrey (UK)
Platform	UoSAT
Mass at launch	49 kg
Dimension	0.68 x 0.34 x 0.34 m
Stabilization	3 axis (gravity gradient)
DC power	EOL: 10 W
Design lifetime	3 years
Frequency chart

Uplink	9600 bps K9NG/G3RUH modulated FSK (FM) AX.25 145.900 145.975 MHz
Downlink	9600 bps K9NG/G3RUH modulated FSK (FM) AX.25 435.120 MHz


 UPMsat 1

Politechnical University of Madrid (UPM in spanish) Satellite

General

Designation	23607 / 95033C
Launch date	7 Jul 1995
Country of origin	Spain
Mission	Technology (microgravity and telecommunications)
Perigee/Apogee	665/675 km
Inclination	98.1°
Period	98.2 min
Launch vehicle	Ariane V75
Mass at launch	47 kg


 Program: USA

Designation used by the United States since mid-1984 to name military spacecrafts.

USA 001	USA 002 = KH 9-19	USA 003 = subsat
USA 004 = SDS 5	USA 005	USA 006
USA 007	USA 008	USA 009 = SDS 6
USA 010	USA 011	USA 012
USA 013 = ITV 1	USA 014 = ITV 2	USA 015
USA 016	USA 017	USA 018
USA 019	USA 020	USA 021 = SDS 7
USA 022	USA 023	USA 024
USA 025	USA 026	USA 027 = KH 11-8
USA 028	USA 029 = DMSP B5D2-4	USA 030
USA 031	USA 032	USA 033 = KH 11-9
USA 034	USA 035	USA 036
USA 037	USA 038	USA 039
USA 040	USA 041	USA 042
USA 043	USA 044	USA 045
USA 046	USA 047	USA 048 = Magnum 2 = Mentor
USA 049	USA 050	USA 051 = LACE
USA 052 = RME	USA 053	USA 054
USA 055 = GLOMR 2	USA 056 = POGS & SSR	USA 057 = TEX
USA 058 = SCE	USA 059	USA 060
USA 061	USA 062	USA 063
USA 064	USA 065	USA 066
USA 067	USA 068 = DMSP B5D2-5	USA 069
USA 070	USA 071	USA 072
USA 073 = DMSP B5D2-6	USA 074	USA 075
USA 076	USA 077	USA 078
USA 079	USA 080	USA 081
USA 082	USA 083	USA 084
USA 085	USA 086	USA 087
USA 088	USA 089	USA 090
USA 091	USA 092	USA 093
USA 094	USA 095	USA 096
USA 097	USA 098	USA 099
USA 100	USA 101	USA 102
USA 103	USA 104	USA 105
USA 106	USA 107	USA 108
USA 109	USA 110	USA 111
USA 112	USA 113	USA 114
USA 115	USA 116


 USA 008

Also called Magnum 1

General

Designation	15543 / 85010B
Launch date	24 Jan 1985
Country of origin	United States
Mission	Military: SIGINT (Magnum)
Geostationary orbit	n/a
Launch vehicle	STS 20
Technical data

Magnum type satellite, built by TRW. Carried a 76 m diameter antenna.

This type of satellite (SIGINT) has seen its performance increase with the diameter of the receiving antenna. Thus the Canyon satellites (1968-72) had 10 m antennas, the Rhyolite (1973-78) and the Jumpseat (1973-78) 18 m, the Vortex (1978-89) 38 m and the Magnum 76 m. The latest generation (Jeroboam) is believed to feature a 150 m diameter antenna!


 USA 032

Also called Singleton 1

General

Designation	19460 / 88078A
Launch date	5 Sep 1988
Country of origin	United States
Mission	Military: SIGINT (Singleton)
Perigee/Apogee	900 km
Inclination	85°
Period
Launch vehicle	Titan 2
Launch site	Vandenberg

Equipped with a 10 m diameter rotating radar, built by TRW, 1500 kg

part of the Wide Area Surveillance System (WASS) of the USAF and US Navy


 USA 040

Also called SDS 2-1

General

Designation	20167 / 89061B
Launch date	8 Aug 1989
Country of origin	United States
Mission	Military:
Perigee/Apogee	n/a
Inclination	n/a
Period	n/a
Launch vehicle	STS 28R


 USA 045

Also called Singleton 2

General

Designation	20220 / 89072A
Launch date	5 Sep 1989
Country of origin	United States
Mission	Military: SIGINT (Singleton)
Perigee/Apogee	900 km
Inclination	85°
Period
Launch vehicle	Titan 2
Launch site	Vandenberg

Equipped with a 10 m diameter rotating radar, built by TRW, 1500 kg

part of the Wide Area Surveillance System (WASS) of the USAF and US Navy

End of life

Out of service	5 Sep 1989
Cause	?


 USA 048

Also called Mentor

General

Designation	20355 / 89090B
Launch date	23 Nov 1989
Country of origin	United States
Mission	Military: SIGINT (Magnum)
Geostationary orbit	n/a
Launch vehicle	STS 33R


 USA 067

Also called AFP 658 or Orion or Magnum 3

General

Designation	20963 / 90097B
Launch date	16 Nov 1990
Country of origin	United States
Mission	Military: SIGINT (Magnum)
Geostationary orbit	n/a
Launch vehicle	STS 38
Mass at launch	2700 kg

Aimed to listen to the Persian Gulf


 USA 081

Also called Singleton 3

General

Designation	21949 / 92023A
Launch date	25 Apr 1992
Country of origin	United States
Mission	Military: SIGINT (Singleton)
Perigee/Apogee	900 km
Inclination	85°
Period
Launch vehicle	Titan 2
Launch site	Vandenberg

Equipped with a 10 m diameter rotating radar, built by TRW, 1500 kg

part of the Wide Area Surveillance System (WASS) of the USAF and US Navy


 USA 089

Also called SDS 2-2

General

Designation	22518 / 92086B
Launch date	2 Dec 1992
Country of origin	United States
Mission	Military: SIGINT?
Perigee/Apogee	n/a Molniya type?
Inclination	n/a
Period	n/a
Launch vehicle	STS 53


 USA 099

Also called Milstar 1-1

General

Designation	22988 / 94009A
Launch date	7 Feb 1994
Country of origin	United States
Mission	Military: Telecommunications
Geostationary orbit	120°W
Launch vehicle	Titan 4

First of the six Milstar geostationary satellites. Buit by Lockheed and operated by the US Space Command. Would be equipped with a Low Data Rate payload with EHF (44.5 GHz) uplink and SHF (20 GHz) downlink and 4 UHF AFSATCOM transponders. Can communicate with Milstar 1-2


 USA 101

Also called P90-5 or TAOS (Technology for Autonomous Operations Survivability) or Step 0

General

Designation	23030 / 94017A
Launch date	13 Mar 1994
Country of origin	United States
Mission	Military: technology
Perigee/Apogee	556/568 km
Inclination	105°
Period	95.9 min
Launch vehicle	Taurus 01
Mass at launch	500 kg

Operated by USAF, built by TRW from an Eagle platform

It carries autonomous navigation systems and a GPS receiver, in an attempt to reduce the need for ground controllers.


 USA 102

Also called Darpasat

General

Designation	23031 / 94017B
Launch date	13 Mar 1994
Country of origin	United States
Mission	Military: technology
Perigee/Apogee	550/550 km ?
Inclination	105° ?
Period	95.9 min ?
Launch vehicle	Taurus 01
Mass at launch	240 kg

Operated by DARPA, built by Ball


 USA 103

Also called Jumpseat adv. 1

General

Designation	23097 / 94026A
Launch date	3 May 1994
Country of origin	United States
Mission	Military: SIGINT (Jumpseat adv.)
Perigee/Apogee	1323/39034 km
Inclination	64.4°
Period	717.9 min
Launch vehicle	Titan 4


 USA 105

Also called Jeroboam 1

General

Designation	23223 / 94054A
Launch date	27 Aug 1994
Country of origin	United States
Mission	Military: SIGINT? (Jeroboam)
Geostationary	n/a
Launch vehicle	Titan 4

Would feature a 150 m diameter antenna, built by Boeing and 4500 kg


 USA 110

Also called Jeroboam 2

General

Designation	23567 / 95022A
Launch date	14 May 1995
Country of origin	United States
Mission	Military: SIGINT? (Jeroboam)
Geostationary orbit	n/a
Launch vehicle	Titan 4

Would feature a 150 m diameter antenna, built by Boeing and 4500 kg


 USA 112

General

Designation	23609 / 95034A
Launch date	10 Jul 1995
Country of origin	United States
Mission	Military: SIGINT (adv. Jumpseat)
Perigee/Apogee	Molniya-like
Inclination	n/a
Period	n/a
Launch vehicle	Titan 4

Is believed similar to USA 103


 USA 115

Also called Milstar 1-2

General

Designation	23712 / 95060A
Launch date	6 Nov 1995
Country of origin	United States
Mission	Military: Telecommunications
Geostationary orbit	n/a
Launch vehicle	Titan 4 #14

The satellite is part of a program of 6 satellites; it is built by the part of Lockheed Martin (formerly Lockheed). This is the second satellite of the 1st block equipped with a Low Data Rate payload with EHF (44.5 GHz) uplink and SHF (20 GHz) downlink and four UHF AFSATCOM transponders. The satellite also has a 60 GHz crosslink to enable it to communicate with Milstar 1-1.

The Milstar program estimated cost is $17.3 billion (1992-2011). Air Force officials said $8.8 billion of the unclassified $17.3 billion portion paid for the six satellites while another $8.5 billion will be spent on new radio gear needed by military units to use the satellites. This satellite is estimated worth $1 billion

Milstar 2 is supposed to test during 6 months before being operational. The next Milstar will be the first Block 2 satellite (in 1999), with a Medium Data Rate payload of three times higher bit rate.

Lockheed Martin Missiles & Space, Sunnyvale, CA, is the prime contractor for Milstar. The Milstar team is led by the MILSATCOM Joint Program Office at the Air Force Space and Missile Systems Center in El Segundo, CA. TRW Space and Electronics Group provides the low data rate payload for the satellite. Hughes Aircraft Company is providing the medium data rate payload for Milstar Block II. When the system becomes fully operational later this year, the U.S. Space Command will manage the worldwide Milstar system from Falcon Air Force Base, Colo.


 Program: Vanguard

American experimental program

Date	Satellite	Launch vehicle
6 Dec 1967	Echec	Test Vehicle 3
5 Feb 1958	Echec	Test Vehicle 3 backup
17 Mar 1958	Vanguard_1	Test Vehicle 4
28 Apr 1958	Echec	Test Vehicle 5
27 May 1958	Echec	Satellite Launch vehicle 1
26 Jun 1958	Echec	Satellite Launch vehicle 2
26 Sep 1958	Echec	Satellite Launch vehicle 3
17 Feb 1959	Vanguard_2	Satellite Launch vehicle 4
13 Apr 1959	Echec	Satellite Launch vehicle 5
22 Jun 1959	Echec	Satellite Launch vehicle 6
18 Sep 1959	Vanguard_3	Test Vehicle 4 backup


Program: Vanguard

Vanguard 1

Vanguard 2

Vanguard 3


 Vanguard 1

Also called grapefruit

General

Designation	00005 / 58002B
Launch date	17 Mar 1958
Country of origin	United States
Mission	Scientific: high atmosphere study
Perigee/Apogee	656/3866 km
Inclination	34.3°
Period	133.2 min
Launch vehicle	Test Vehicle 4
Launch site	Cape Canaveral
Mass at launch	1.47 kg

Sphere of 16 cm diameter. Carries a temperature sounder and a radio transmitter.


 Vanguard 2

General

Designation	00011 / 59001A
Launch date	17 Feb 1959
Country of origin	United States
Mission	Scientific: high atmosphere study
Perigee/Apogee	559/3047 km
Inclination	32.9°
Period	122.7 min
Launch vehicle	Satellite Launch vehicle 4
Launch site	Cape Canaveral


 Vanguard 3

General

Designation	00020 / 59007A
Launch date	18 Sep 1959
Country of origin	United States
Mission	Scientific: Sun study
Perigee/Apogee	512/3412 km
Inclination	33.3°
Period	126.3 min
Launch vehicle	Test Vehicle 4 backup
Launch site	Cape Canaveral


Program: Vela
 Vela

American satellites to check the 1963 Moscow treaty: no atmospheric atomic explosions


 Viking

General

Designation	16614 / 86019B
Launch date	22 Feb 1986
Country of origin	Sweden
Operator	Swedish Space Corp.
Mission	Scientific: ionosphere and magnetosphere study
Perigee/Apogee	818/13521 km
Inclination	98.8°
Period	261.6 min
Launch vehicle	Ariane V16

Designed to measure space plasma phenomena in the Earth's magnetosphere and produce UV images of the auroral zone. By September 1986 it had taken 20,000 images of the complete aurora.

Cost: $18 million

Technical data

Specifications

Prime contractor	Saab Space
Mass at launch	538 kg
Payload mass	60 kg
Diameter	1.9 m
Height	0.5 m
DC power	80 W
Stabilization	magneto-torquers (3 rpm)
Design lifetime	8 months
Payload

2 UV imagers & instruments to measure electric and magnetic fields, charged particles, and wave/particle interaction in the magnetosphere

Telemetry/data	S-band
Data rate	55 kbps
RF power	2.5 W


 Program: Vortex

Also called Chalet

American geostationary SIGINT satellites. Equipped with a 38 m antenna.


Program: Vortex

Vortex 1

Vortex 2

Vortex 3

Vortex 4

Vortex 5

Vortex 6


 Vortex 1

General

Designation	10941 / 78058A
Launch date	10 Jun 1978
Country of origin	United States
Mission	Military: SIGINT
Geostationary orbit	n/a
Launch vehicle
Launch site	Cape Canaveral


 Vortex 2

General

Designation	11558 / 79086A
Launch date	1 Oct 1979
Country of origin	United States
Mission	Military: SIGINT
Geostationary orbit	n/a
Launch vehicle
Launch site	Cape Canaveral


 Vortex 3

General

Designation	12930 / 81107A
Launch date	31 Oct 1981
Country of origin	United States
Mission	Military: SIGINT
Geostationary orbit	n/a
Launch vehicle
Launch site	Cape Canaveral


 Vortex 4

General

Designation	14675 / 84009A
Launch date	31 Jan 1984
Country of origin	United States
Mission	Military: SIGINT
Geostationary orbit	n/a
Launch vehicle
Launch site	Cape Canaveral


 Vortex 5

Also called USA 031

General

Designation	19458 / 88077A
Launch date	2 Sep 1988
Country of origin	United States
Mission	Military: SIGINT
Geostationary orbit	n/a
Launch vehicle
Launch site	Cape Canaveral


 Vortex 6

Also called USA 037

General

Designation	19976 / 89035A
Launch date	10 May 1989
Country of origin	United States
Mission	Military: SIGINT
Geostationary orbit	n/a
Launch vehicle
Launch site	Cape Canaveral


 Webersat

Also called Microsat 3 or WO-18 or Oscar 18

General

Designation	20441 / 90005F
Launch date	22 Jan 1990
Country of origin	United States
Mission	Telecommunications
Perigee/Apogee	780/797 km
Inclination	98.6°
Period	100.6 min
Launch vehicle	Ariane V35

Designed at Weber State College (Ogden, Utah, USA), based on an Amsat-NA Microsat bus

Technical data

Uplink	1200 bps Manchester coded (Biphase-L) FSK (FM) AX.25 145.900 MHz
	NTSC modulated ATV (not in use?) 1265.000 MHz
Downlink	1200 bps BPSK (SSB) AX.25, either one of the two frequencies below: 437.075 MHz (LHCP in northern hemisphere), normal unfiltered PSK 437.102 MHz (RHCP in northern hemisphere), Raised Cosine modulation


 Program: Westar

American telecommunication program operated by the Western Union Telegraph and since 1988 by Hughes.


Program: Westar

Westar 1

Westar 2

Westar 3

Westar 4

Westar 5

Westar 6


Westar 1, 2 & 3's specifications

Mass at launch	572 kg
Mass in orbit	208 kg
Diameter
Height
Stabilization	Spin stabilized
DC power
Design lifetime	7 years
Capacity	14400 phone circuits


Westar 1, 2 & 3's C-band

Main transponders	12
Backup transponders
Power
Bandwidth	36 MHz
Coverage
EIRP	33 dBW
Polarization


Westar 4, 5 & 6's specifications

Prime contractor	Hughes
Platform	HS-376
Mass at launch	1100 kg
Mass in orbit	585 kg
Diameter	2.16 m
Height	6.6 m deployed
Stabilization	Spin stabilized
DC power	BOL: 820 W EOL: 700 W
Design lifetime	10 years


Westar 4, 5 & 6's C-band

Main transponders	24
Backup transponders
Power	7.5 W (TWTA)
Bandwidth	36 MHz
Coverage
EIRP	34 dBW
Polarization


 Westar 1

General

Designation	07250 / 74022A
Launch date	13 Apr 1974
Country of origin	United States
Mission	Telecommunications
Geostationary orbit	99°W
Launch vehicle	Thor Delta #101
Launch site	Cape Canaveral
End of life

Out of service	yes
Technical data

Specifications

C-band


 Westar 2

General

Designation	07466 / 74075A
Launch date	10 Oct 1974
Country of origin	United States
Mission	Telecommunications
Geostationary orbit	125°W
Launch vehicle	Thor Delta #103
Launch site	Cape Canaveral
End of life

Out of service	yes
Technical data

Specifications

C-band


 Westar 3

General

Designation	11484 / 79072A
Launch date	10 Aug 1979
Country of origin	United States
Mission	Telecommunications
Geostationary orbit	91°W
Launch vehicle	Thor Delta #149
Launch site	Cape Canaveral
End of life

Out of service	yes
Technical data

Specifications

C-band


 Westar 4

General

Designation	13069 / 82014A
Launch date	26 Feb 1982
Country of origin	United States
Mission	Telecommunications
Geostationary orbit	99°W
Launch vehicle	Thor Delta #160
Launch site	Cape Canaveral
End of life

Out of service	late 1991
Technical data

Specifications

C-band


 Westar 5

General

Designation	13269 / 82058A
Launch date	9 Jun 1982
Country of origin	United States
Mission	Telecommunications
Geostationary orbit	122.5°W
Launch vehicle	Thor Delta #162
Launch site	Cape Canaveral
End of life

Out of service	yes
Technical data

Specifications

C-band


 Westar 6

General

Designation	14688 / 84011B
Launch date	3 Feb 1984
Country of origin	United States
Mission	Telecommunications
Geostationary orbit	n/a
Launch vehicle	STS 11

Placed on a bad orbit, it was retrieved on 16 Nov 1984 by STS 19. It then became Asiasat 1.

Technical data

Specifications

C-band


 Dial-Wika

Wissenschaftlich Kapsel

General

Designation	04344 / 70017A
Launch date	10 Mar 1970
Country of origin	Germany
Mission	Scientific: high atmosphere study
Perigee/Apogee	301/1631 km
Inclination	5.4°
Period	104.2 min
Launch vehicle	Diamant #5

First launch from Kourou

End of life

Decay	5 Oct 1978


 Wind 1

General

Designation	23333 / 94071A
Launch date	1 Nov 1994 at 09:31 UT
Country of origin	United States
Operator	NASA (part of the Global Geospace Science program)
Mission	Scientific: study of Sun
Perigee/Apogee	n/a
Inclination	n/a
Period	n/a
Launch vehicle	Delta 2 #227
Mass at launch	1200 kg

Cost: $173 million, Launched under the MELVS contract

Wind is a spacecraft in the International Solar-Terrestrial Program (ISTP). It carried instruments to measure the solar wind plasma and magnetic field, besides several instruments to measure very energetic particles and gamma rays. Operates together with Polar

After several orbits extending to close proximity of the Moon (at about 60 Earth-radii) and involving several thrust-firings during that phase, the spacecraft will eventually reach the first Lagrangian point (L-1) located at about 275 Earth-radii in the Sun-ward direction and orbit around that point. Orbital parameters are very variable even during the first two years.

Built by Martin Marietta Astra Space


Program: Wordstar
 Program: Worldstar

American program operated by Worldspace, Washington to reach the third World with digital radio sent by 3 satelllites. The satellites will be constructed by a consortium led by Alcatel Espace and launched from 1998 on. They will use L-band in DAB mode. The Digital Audio Broadcasting service will transmit to a new generation of receiver called Starman, which will have a satellite antenna the size of a business card. It's been developed by Motorola.


Program: Worldstar

Afristar

Asiastar

Caribstar


Worldstar's specifications

Prime contractor	Alcatel Espace
Platform
Mass at launch	2700 kg
Mass in orbit
Dimension
Solar array
Stabilization
DC power
Design lifetime	15 years


Worldstar's L-band

Main transponders	288 channels
Backup transponders
Power
Bandwidth	16 kbps per channel
Coverage	3 beams with 96 channels each
EIRP
Polarization
Frequencies	Upload: 7.05 - 7.075 GHz (SCPC) Downlink: 1.467 - 1.492 GHz

a mono voice-only service requires 1 channel

a mono music service requires 2 channels

a stereo service requires 4 channels


 Wresat

General

Designation	03054 / 67118A
Launch date	29 Nov 1967
Country of origin	Australia
Mission	Scientific: high atmosphere and sun?
Perigee/Apogee	198/1252 km
Inclination	83.3°
Period	99.3 min
Launch vehicle	Redstone (US)
Launch site	Woomera
Mass at launch	50 kg


 WSF 2

Wake Shield Facility

General

Designation	23669 / 95048C
Launch date	11 Sep 1995 at 11:25 UT
Country of origin	United States
Mission	Scientific: Microgravity
Perigee/Apogee	370 km
Inclination	28.4°
Period	91.9 min
Launch vehicle	STS 69
Mass at launch	1979 kg

The WSF Free Flyer generates an ultra-hard vacuum in its wake for production of semiconductors and other experiments. WSF is built and operated by the Space Vacuum Epitaxy Center in Houston.

Was troubled by control problems and overheating.

End of life

Out of service	14 Sep 1995
Reentry	18 Sep 1995 with STS 69


 XTE

X-ray Timing Explorer, Also called RXTE (Bruno B. Rossi X-ray Timing Explorer)

General

Designation	23757 / 95074A
Launch date	30 Dec 1995 13:48 UT
Country of origin	United States
Mission	Scientific: X-ray astronomy
Perigee/Apogee	565/583 km
Inclination	23°
Period	96.1 min
Launch vehicle	Delta 2 #230

Cost: $195 million, Launched under the MELVS contract

Delta's new avionics system will use an array of redundant laser gyros and accelerometers to sense the vehicle's velocity and attitude movement, which includes its angular position and direction. The avionics system feeds data to onboard computers which control Delta 2's engines and power, engine start, main engine cutoff, staging and payload separation. The avionics system now has two power sources and is completely redundant. If one data system is lost, the other will complete the mission.

Contact

http://heasarc.gsfc.nasa.gov/docs/xte/

Technical data

Specifications

Built under coordination of NASA-Goddard Space Flight Center. It includes two high gain antennae, allowing an almost continuous telemetry stream using TDRS's Multiple Access mode.

Proportional Counter Array (PCE)

Instrument with large collecting area but low spatial resolution, for accurate timing and spectral measurements of bright X-ray sources. Built by the LHEA at GSFC

The PCA is an array of five proportional counters with a total collecting area of 6500 square cm. The instrumental properties are:

Energy range	2 - 60 keV
Energy resolution	&< 18% at 6 keV
Time resolution	1 microsec
Spatial resolution	collimator with 1 degree FWHM
Detectors	5 proportional counters
Collecting area	6500 square cm
Layers	1 Propane veto; 3 Xenon, each split into two; 1 Xenon veto layer
Sensitivity	0.1 mCrab
Background	2 mCrab

Events detected by the PCA will be processed on board by the EDS before insertion into the telemetry stream.

High Energy X-ray Timing Experiment (HEXTE)

Intrument built by CASS at UCSD which will study X-rays. HEXTE consists of two clusters each containing four phoswich scintillation counters. The clusters can rock at right angles to each other, with amplitudes of 1.5 or 3 degrees, to provide accurate background measurements. The total collecting area is 1600 square cm. The instrumental properties are:

Energy range	20 - 250 keV
Energy resolution	&< 18% at 60 keV
Time resolution	10 microsec
Spatial resolution	collimator with 1 degree FWHM
Detectors	2 times 4 scintillation counters
Collecting area	1600 square cm
Phoswich	NaI / CsI
Sensitivity	10 mCrab
Background	100 mCrab

Events detected by HEXTE will be processed on board by its own data system before insertion into the telemetry stream. It will allow event mode, histogram binned mode, multiscalar mode, PHA/PSA spectral mode, and burst mode formats.

All-Sky Monitor (ASM)

ASM, built by the CSR at MIT, will spot X-ray flare stars and burst sources. It consists of three wide-angle shadow cameras equipped with proportional counters with a total collecting area of 90 square cm. The instrumental properties are:

Energy range	2 - 10 keV
Time resolution	80% of the sky every 90 minutes
Spatial resolution	3' x 15'
Number of shadow cameras	3, each with 6 x 90 degrees FOV
Collecting area	90 square cm
Detector	Xenon proportional counter, position-sensitive
Sensitivity	30 mCrab

Events detected by the ASM will be processed on board by the EDS before insertion into the telemetry stream.

Experiment Data System (EDS)

The EDS consists of eight Event Analyzers (EA), of which two are dedicated to the PCA and six to the ASM. Each EA contains an Intel 80286 processor and associated memory. The EAs can be programmed independently to process incoming events from the instruments in any of the following modes:

Transparent mode, using 1, 2, or 3 EAs

Event mode, using 1 or 2 EAs

Binned mode (time and/or energy)

Burst catcher mode

Fourier transform mode

Pulsar fold mode

Autocorrelation mode

Arrival time differences histogram mode

It is being built by the CSR at MIT.

Downlink frequency

2287.500 MHz


 Program: Yamal

Program of 2 Russian-built communication satellites operated by GasCom Corporation (Moscow). GasCom is a joint venture between RAO "Gazprom", the Russian natural gas monopoly, and RKK "Energia", the Russian aerospace company (design and operation of Mir).

Satellites are to be launched in early 1997.

Slots reserved are: 19.5°W and 75°E

The communications payload and other electronic equipment are to be provided by Space Systems/Loral. The contract is believed to be the first commercial procurement of Western satellite equipment by a Russian company, and is the first sale of operational flight equipment by SS/L to Russia.

The satellites will be geostationary, 1300 kg. The bus is called Yamal


 Program: Yuri

Means "tiger lily"

Japanese telecommunication program operated by NHK (or Telecommunication Satellite Corporation of Japan?)


Program: Yuri

Yuri 1

Yuri 2A

Yuri 2B

Yuri 2X

Yuri 3A

Yuri 3B

Yuri 3H

Yuri 3N


Yuri 2's specifications

Prime contractor	Toshiba with GE Astro Space
Platform	GE 3000
Mass at launch	1290 kg
Mass in orbit	760 kg
Dimension	1.2 x 1.32 x 2.89 m
Stabilization	3 axis
DC power	BOL: 1400 W
Design lifetime	5 years


Yuri 2's Ku-band

Main transponders	2
Backup transponders	1
Power	100 W (TWTA)
Bandwidth	27 MHz
Coverage
EIRP	54 dBW
Polarization


Yuri 3's specifications

Prime contractor	NEC with GE Astro Space
Platform	GE 3000
Mass at launch	1115 kg
Mass in orbit	550 kg
Dimension	1.63 x 1.32 x 0.99 m
Solar array	14.3 m span
Stabilization	3 axis
DC power	BOL: 1443 W
Design lifetime	7 years


Yuri 3's Ku-band

Main transponders	3
Backup transponders	3
Power	120 W (TWTA)
Bandwidth	27 MHz
Coverage
EIRP	54 dBW
Polarization


 Yuri 1

Also called BS E

General

Designation	10792 / 78039A
Launch date	7 Apr 1978
Country of origin	Japan
Mission	Telecommunications
Geostationary orbit	110°E
Launch vehicle	Thor Delta #140
Launch site	Cape Canaveral
End of life

Out of service	January 1982


 Yuri 2A

Also called BS 2A

General

Designation	14659 / 84005A
Launch date	23 Jan 1984
Country of origin	Japan
Mission	Telecommunications
Geostationary orbit	110°E
Launch vehicle	N2
Launch site	Tanegashima

Suffered from in-orbit equipment failures

End of life

Out of service	yes
Technical data

Specifications

Ku-band


 Yuri 2B

Also called BS 2B

General

Designation	16597 / 86016A
Launch date	12 Feb 1986
Country of origin	Japan
Mission	Telecommunications
Geostationary orbit	110°E
Launch vehicle	N2
Launch site	Tanegashima
End of life

Out of service	yes
Technical data

Specifications

Ku-band

2 out of 3 transponders failed 3 months after launch


 Yuri 2X

Also called BS 2X

End of life

Out of service	23 Feb 1990
Cause	Explosed with Ariane V36
Technical data

Specifications

Ku-band


 Yuri 3A

Also called BS 3A

General

Designation	20771 / 90077A
Launch date	28 Aug 1990
Country of origin	Japan
Mission	Telecommunications
Geostationary orbit	110°E
Launch vehicle	H1
Launch site	Tanegashima

Started having stability problems in Sep 1995 with a peak in November. Traffic had to be taken over by Yuri 3N which is less powerful.

Technical data

Specifications

Ku-band


 Yuri 3H

Also called BS 3H

General

Launch date	19 Apr 1991
Country of origin	Japan
Mission	Telecommunications
Geostationary orbit
Launch vehicle	Atlas Centaur #070
End of life

Out of service	19 Apr 1991
Cause	Launch failure

This satellite was a replacement for the Yuri 2X spacecraft which failed and was in turn a replacement for Yuri 2A spacecraft in orbit which had been suffering equipment failures.

Technical data

Specifications

Ku-band


 Yuri 3B

Also called BS 3B

General

Designation	21668 / 91060A
Launch date	25 Aug 1991
Country of origin	Japan
Mission	Telecommunications
Geostationary orbit	110°E
Launch vehicle	H1
Launch site	Tanegashima
Technical data

Specifications

Ku-band


 Yuri 3N

Also called BS 3N

General

Designation	23176 / 94040B
Launch date	8 Jul 1994
Country of origin	Japan
Mission	Telecommunications
Geostationary orbit	110°E
Launch vehicle	Ariane V65
Mass at launch	1210 kg
Technical data

Specifications

Ku-band

Equipped with a Star 30BP apogee motor


 Program: Cosmos

Soviet denomination for satellites part of plenty of different programs. Some have a specific fact sheet in TSE:

Sub programs

Eorsat

Glonass

Geizer

Luch

Parus

Rorsat

Tsikada


 Cosmos 0001

Also called Sputnik 11

General

Designation	00266 / 62008A
Launch date	16 Mar 1962
Country of origin	CIS
Mission	Scientific: ionosphere study
Perigee/Apogee	207/649 km
Inclination	49°
Period	93.1 min
Launch vehicle
Launch site	Kapustin Yar
End of life

Decay	25 May 1962


 Cosmos 0100

General

Designation	01843 / 65106A
Launch date	17 Dec 1965
Country of origin	CIS
Mission
Perigee/Apogee	485/547 km
Inclination	65°
Period	95 min
Launch vehicle
Launch site	Tyuratam


 Cosmos 0110

General

Designation	02070 / 66015A
Launch date	22 Feb 1966
Country of origin	CIS
Mission
Perigee/Apogee	181/887 km
Inclination	51.8°
Period	95.3 min
Launch vehicle
Launch site	Tyuratam

Study of animals and vegetals in space

End of life

Decay	16 Mar 1966


 Cosmos 0122

General

Designation	02254 / 66057A
Launch date	25 Jun 1966
Country of origin	CIS
Mission	Meteorology
Perigee/Apogee	371/388 km
Inclination	65°
Period	92.1 min
Launch vehicle
Launch site	Tyuratam

First soviet meteorology satellite

End of life

Decay	14 Nov 1989
Technical data

Specifications


 Cosmos 0144

General

Designation	02695 / 67018A
Launch date	28 Feb 1967
Country of origin	CIS
Mission	Meteorology
Perigee/Apogee	574/644 km
Inclination	81.3°
Period	96.9 min
Launch vehicle
Launch site	Plesetsk
End of life

Decay	14 Sep 1982
Technical data

Specifications


 Cosmos 0169

General

Designation	02878 / 67069A
Launch date	17 Jul 1967
Country of origin	CIS
Mission
Perigee/Apogee	135/200 km
Inclination	49.7°
Period	87.8 min
Launch vehicle
Launch site	Tyuratam
End of life

Decay	17 Jul 1967


 Cosmos 0186

General

Designation	03014 / 67105A
Launch date	27 Oct 1967
Country of origin	CIS
Mission
Perigee/Apogee	179/223 km
Inclination	51.6°
Period	88.6 min
Launch vehicle
Launch site	Tyuratam

Docked with Cosmos 0188

End of life

Decay	31 Oct 1967


 Cosmos 0188

General

Designation	03020 / 67107A
Launch date	30 Oct 1967
Country of origin	CIS
Mission
Perigee/Apogee	180/247 km
Inclination	51.7°
Period	88.7 min
Launch vehicle
Launch site	Tyuratam

Docked with Cosmos 0186

End of life

Decay	2 Nov 1967


 Cosmos 0368

General

Designation	04571 / 70080A
Launch date	8 Oct 1970
Country of origin	CIS
Mission
Perigee/Apogee	202/383 km
Inclination	65°
Period	90.4 min
Launch vehicle
Launch site	Tyuratam

Study of animals and vegetals in space

End of life

Decay	14 Oct 1970


 Cosmos 0444

General

Designation	05547 / 71086A
Launch date	13 Oct 1971
Country of origin	CIS
Mission	Telecommunications
Perigee/Apogee	1318/1507 km
Inclination	74°
Period	114.1 min
Launch vehicle
Launch site	Plesetsk


 Cosmos 0445

General

Designation	05548 / 71086B
Launch date	13 Oct 1971
Country of origin	CIS
Mission	Telecommunications
Perigee/Apogee	1348/1509 km
Inclination	74°
Period	114.4 min
Launch vehicle
Launch site	Plesetsk


 Cosmos 0446

General

Designation	05549 / 71086C
Launch date	13 Oct 1971
Country of origin	CIS
Mission	Telecommunications
Perigee/Apogee	1378/1509 km
Inclination	74°
Period	114.8 min
Launch vehicle
Launch site	Plesetsk


 Cosmos 0447

General

Designation	05550 / 71086D
Launch date	13 Oct 1971
Country of origin	CIS
Mission	Telecommunications
Perigee/Apogee	1408/1512 km
Inclination	74°
Period	115.1 min
Launch vehicle
Launch site	Plesetsk


 Cosmos 0448

General

Designation	05551 / 71086E
Launch date	13 Oct 1971
Country of origin	CIS
Mission	Telecommunications
Perigee/Apogee	1438/1514 km
Inclination	74°
Period	115.5 min
Launch vehicle
Launch site	Plesetsk


 Cosmos 0449

General

Designation	05552 / 71086F
Launch date	13 Oct 1971
Country of origin	CIS
Mission	Telecommunications
Perigee/Apogee	1480/1540 km
Inclination	74°
Period	116.2 min
Launch vehicle
Launch site	Plesetsk


 Cosmos 0450

General

Designation	05553 / 71086G
Launch date	13 Oct 1971
Country of origin	CIS
Mission	Telecommunications
Perigee/Apogee	1460/1527 km
Inclination	74°
Period	115.8 min
Launch vehicle
Launch site	Plesetsk


 Cosmos 0451

General

Designation	05554 / 71086H
Launch date	13 Oct 1971
Country of origin	CIS
Mission	Telecommunications
Perigee/Apogee	1487/1571 km
Inclination	74°
Period	116.6 min
Launch vehicle
Launch site	Plesetsk


 Cosmos 0500

General

Designation	06097 / 72053A
Launch date	10 Jul 1972
Country of origin	CIS
Mission
Perigee/Apogee	505/548 km
Inclination	74°
Period	95.2 min
Launch vehicle
Launch site	Plesetsk
End of life

Decay	29 Mar 1980


 Cosmos 0504

General

Designation	06117 / 72057A
Launch date	20 Jul 1972
Country of origin	CIS
Mission	Telecommunications
Perigee/Apogee	1319/1493 km
Inclination	74°
Period	113.9 min
Launch vehicle
Launch site	Plesetsk


 Cosmos 0505

General

Designation	06118 / 72057B
Launch date	20 Jul 1972
Country of origin	CIS
Mission	Telecommunications
Perigee/Apogee	1349/1494 km
Inclination	74°
Period	114.3 min
Launch vehicle
Launch site	Plesetsk


 Cosmos 0506

General

Designation	06119 / 72057C
Launch date	20 Jul 1972
Country of origin	CIS
Mission	Telecommunications
Perigee/Apogee	1380/1494 km
Inclination	74°
Period	114.6 min
Launch vehicle
Launch site	Plesetsk


 Cosmos 0507

General

Designation	06120 / 72057D
Launch date	20 Jul 1972
Country of origin	CIS
Mission	Telecommunications
Perigee/Apogee	1409/1494 km
Inclination	74°
Period	114.9 min
Launch vehicle
Launch site	Plesetsk


 Cosmos 0508

General

Designation	06121 / 72057E
Launch date	20 Jul 1972
Country of origin	CIS
Mission	Telecommunications
Perigee/Apogee	1441/1493 km
Inclination	74°
Period	115.3 min
Launch vehicle
Launch site	Plesetsk


 Cosmos 0509

General

Designation	06122 / 72057F
Launch date	20 Jul 1972
Country of origin	CIS
Mission	Telecommunications
Perigee/Apogee	1471/1496 km
Inclination	74°
Period	115.6 min
Launch vehicle
Launch site	Plesetsk


 Cosmos 0510

General

Designation	06123 / 57057G
Launch date	20 Jul 1972
Country of origin	CIS
Mission	Telecommunications
Perigee/Apogee	1493/1507 km
Inclination	74°
Period	116 min
Launch vehicle
Launch site	Plesetsk


 Cosmos 0511

General

Designation	06124 / 72057H
Launch date	20 Jul 1972
Country of origin	CIS
Mission	Telecommunications
Perigee/Apogee	1493/1543 km
Inclination	74°
Period	116.4 min
Launch vehicle
Launch site	Plesetsk


 Cosmos 0588

General

Designation	06845 / 73069A
Launch date	2 Oct 1973
Country of origin	CIS
Mission	Telecommunications
Perigee/Apogee	1446/1490 km
Inclination	74°
Period	155.3 min
Launch vehicle
Launch site	Plesetsk


 Cosmos 0589

General

Designation	06846 / 73069B
Launch date	2 Oct 1973
Country of origin	CIS
Mission	Telecommunications
Perigee/Apogee	1412/1486 km
Inclination	74°
Period	114.9 min
Launch vehicle
Launch site	Plesetsk


 Cosmos 0590

General

Designation	06847 / 73069C
Launch date	2 Oct 1973
Country of origin	CIS
Mission	Telecommunications
Perigee/Apogee	1431/1485 km
Inclination	74°
Period	115.1 min
Launch vehicle
Launch site	Plesetsk


 Cosmos 0591

General

Designation	06848 / 73069D
Launch date	2 Oct 1973
Country of origin	CIS
Mission	Telecommunications
Perigee/Apogee	1344/1483 km
Inclination	74°
Period	114.4 min
Launch vehicle
Launch site	Plesetsk


 Cosmos 0592

General

Designation	06849 / 73069E
Launch date	2 Oct 1973
Country of origin	CIS
Mission	Telecommunications
Perigee/Apogee	1328/1482 km
Inclination	74°
Period	133.9 min
Launch vehicle
Launch site	Plesetsk


 Cosmos 0593

General

Designation	06850 / 73069F
Launch date	2 Oct 1973
Country of origin	CIS
Mission	Telecommunications
Perigee/Apogee	1361/1483 km
Inclination	74°
Period	114.3 min
Launch vehicle
Launch site	Plesetsk


 Cosmos 0594

General

Designation	06851 / 73069G
Launch date	2 Oct 1973
Country of origin	CIS
Mission	Telecommunications
Perigee/Apogee	1378/1484 km
Inclination	74°
Period	114.5 min
Launch vehicle
Launch site	Plesetsk


 Cosmos 0595

General

Designation	06852 / 73069H
Launch date	2 Oct 1973
Country of origin	CIS
Mission	Telecommunications
Perigee/Apogee	1396/1483 km
Inclination	74°
Period	114.7 min
Launch vehicle
Launch site	Plesetsk


 Cosmos 0596

General

Designation	06856 / 73070A
Launch date	3 Oct 1973
Country of origin	CIS
Mission	spying?
Perigee/Apogee	206/287 km
Inclination	65.4°
Period	89.4 min
Launch vehicle
Launch site	Plesetsk
End of life

Decay	9 Oct 1973


 Cosmos 0597

General

Designation	06858 / 73071A
Launch date	6 Oct 1973
Country of origin	CIS
Mission	spying?
Perigee/Apogee	206/290 km
Inclination	65.4°
Period	89.5 min
Launch vehicle
Launch site	Plesetsk
End of life

Decay	12 Oct 1973


 Cosmos 0598

General

Designation	06862 / 73072A
Launch date	10 Oct 1973
Country of origin	CIS
Mission	spying?
Perigee/Apogee	208/334 km
Inclination	72.8°
Period	89.9 min
Launch vehicle
Launch site	Plesetsk
End of life

Decay	16 Oct 1973


 Cosmos 0599

General

Designation	06867 / 73073A
Launch date	15 Oct 1973
Country of origin	CIS
Mission	spying?
Perigee/Apogee	202/280 km
Inclination	64.9°
Period	89.3 min
Launch vehicle
Launch site	Plesetsk
End of life

Decay	28 Oct 1973


 Cosmos 0600

General

Designation	06873 / 73074A
Launch date	16 Oct 1973
Country of origin	CIS
Mission	spying?
Perigee/Apogee	205/340 km
Inclination	72.8°
Period	90 min
Launch vehicle
Launch site	Plesetsk
End of life

Decay	23 Oct 1973


 Cosmos 0605

General

Designation	06913 / 73083A
Launch date	31 Oct 1973
Country of origin	CIS
Mission
Perigee/Apogee	213/403 km
Inclination	62.8°
Period	90.7 min
Launch vehicle
Launch site	Plesetsk

Study of animals and vegetals in space

End of life

Decay	22 Nov 1973


 Cosmos 0637

General

Designation	07229 / 74017A
Launch date	26 Mar 1974
Country of origin	CIS
Mission	Military: Telecommunications
Perigee/Apogee	35475/35819 km, 65°E
Inclination	13,7°
Period	1429 min
Launch vehicle	Proton #46

First Soviet geostationary satellite


 Cosmos 0641

General

Designation	07265 / 74024A
Launch date	23 Apr 1974
Country of origin	CIS
Mission	Telecommunications
Perigee/Apogee	1385/1479 km
Inclination	74°
Period	114.5 min
Launch vehicle
Launch site	Plesetsk


 Cosmos 0642

General

Designation	07266 / 74024B
Launch date	23 Apr 1974
Country of origin	CIS
Mission	Telecommunications
Perigee/Apogee	1316/1478 km
Inclination	74°
Period	113.7 min
Launch vehicle
Launch site	Plesetsk


 Cosmos 0643

General

Designation	07267 / 74024C
Launch date	23 Apr 1974
Country of origin	CIS
Mission	Telecommunications
Perigee/Apogee	1350/1479 km
Inclination	74°
Period	114.4 min
Launch vehicle
Launch site	Plesetsk


 Cosmos 0644

General

Designation	07268 / 74024D
Launch date	23 Apr 1974
Country of origin	CIS
Mission	Telecommunications
Perigee/Apogee	1332/1479 km
Inclination	74°
Period	113.9 min
Launch vehicle
Launch site	Plesetsk


 Cosmos 0645

General

Designation	07269 / 74024E
Launch date	23 Apr 1974
Country of origin	CIS
Mission	Telecommunications
Perigee/Apogee	1367/1479 km
Inclination	74°
Period	114.3 min
Launch vehicle
Launch site	Plesetsk


 Cosmos 0646

General

Designation	07270 / 74024F
Launch date	23 Apr 1974
Country of origin	CIS
Mission	Telecommunications
Perigee/Apogee	1402/1482 km
Inclination	74°
Period	114.7 min
Launch vehicle
Launch site	Plesetsk


 Cosmos 0647

General

Designation	07271 / 74024G
Launch date	23 Apr 1974
Country of origin	CIS
Mission	Telecommunications
Perigee/Apogee	1420/1481 km
Inclination	74°
Period	114.9 min
Launch vehicle
Launch site	Plesetsk


 Cosmos 0648

General

Designation	07272 / 74024H
Launch date	23 Apr 1974
Country of origin	CIS
Mission	Telecommunications
Perigee/Apogee	1435/1487 km
Inclination	74°
Period	115.1 min
Launch vehicle
Launch site	Plesetsk


 Cosmos 0677

General

Designation	07435 / 74072A
Launch date	19 Sep 1974
Country of origin	CIS
Mission	Telecommunications
Perigee/Apogee	1394/1464 km
Inclination	74°
Period	114.4 min
Launch vehicle
Launch site	Plesetsk


 Cosmos 0678

General

Designation	07436 / 74072B
Launch date	19 Sep 1974
Country of origin	CIS
Mission	Telecommunications
Perigee/Apogee	1464/1530 km
Inclination	74°
Period	115.9 min
Launch vehicle
Launch site	Plesetsk


 Cosmos 0679

General

Designation	07437 / 74072C
Launch date	19 Sep 1974
Country of origin	CIS
Mission	Telecommunications
Perigee/Apogee	1464/1508 km
Inclination	74°
Period	115.7 min
Launch vehicle
Launch site	Plesetsk


 Cosmos 0680

General

Designation	07438 / 74072D
Launch date	19 Sep 1974
Country of origin	CIS
Mission	Telecommunications
Perigee/Apogee	1464/1489 km
Inclination	74°
Period	115.5 min
Launch vehicle
Launch site	Plesetsk


 Cosmos 0681

General

Designation	07439 / 74072E
Launch date	19 Sep 1974
Country of origin	CIS
Mission	Telecommunications
Perigee/Apogee	1463/1470 km
Inclination	74°
Period	115.3 min
Launch vehicle
Launch site	Plesetsk


 Cosmos 0682

General

Designation	07440 / 74072F
Launch date	19 Sep 1974
Country of origin	CIS
Mission	Telecommunications
Perigee/Apogee	1450/1464 km
Inclination	74°
Period	115 min
Launch vehicle
Launch site	Plesetsk


 Cosmos 0683

General

Designation	07441 / 74072G
Launch date	19 Sep 1974
Country of origin	CIS
Mission	Telecommunications
Perigee/Apogee	1432/1464 km
Inclination	74°
Period	114.8 min
Launch vehicle
Launch site	Plesetsk


 Cosmos 0684

General

Designation	07442 / 74072H
Launch date	19 Sep 1974
Country of origin	CIS
Mission	Telecommunications
Perigee/Apogee	1413/1464 km
Inclination	74°
Period	114.6 min
Launch vehicle
Launch site	Plesetsk


 Cosmos 0711

General

Designation	07678 / 75016A
Launch date	28 Feb 1975
Country of origin	CIS
Mission	Telecommunications
Perigee/Apogee	1459/1490 km
Inclination	74°
Period	115.4 min
Launch vehicle
Launch site	Plesetsk


 Cosmos 0712

General

Designation	07679 / 75016B
Launch date	28 Feb 1975
Country of origin	CIS
Mission	Telecommunications
Perigee/Apogee	1409/1488 km
Inclination	74°
Period	114.8 min
Launch vehicle
Launch site	Plesetsk


 Cosmos 0713

General

Designation	07680 / 75016C
Launch date	28 Feb 1975
Country of origin	CIS
Mission	Telecommunications
Perigee/Apogee	1393/1485 km
Inclination	74°
Period	114.6 min
Launch vehicle
Launch site	Plesetsk


 Cosmos 0714

General

Designation	07681 / 75016D
Launch date	28 Feb 1975
Country of origin	CIS
Mission	Telecommunications
Perigee/Apogee	1442/1489 km
Inclination	74°
Period	115.2 min
Launch vehicle
Launch site	Plesetsk


 Cosmos 0715

General

Designation	07682 / 75016E
Launch date	28 Feb 1975
Country of origin	CIS
Mission	Telecommunications
Perigee/Apogee	1467/1502 km
Inclination	74°
Period	115.7 min
Launch vehicle
Launch site	Plesetsk


 Cosmos 0716

General

Designation	07683 / 75016F
Launch date	28 Feb 1975
Country of origin	CIS
Mission	Telecommunications
Perigee/Apogee	1477/1512 km
Inclination	74°
Period	115.9 min
Launch vehicle
Launch site	Plesetsk


 Cosmos 0717

General

Designation	07684 / 75016G
Launch date	28 Feb 1975
Country of origin	CIS
Mission	Telecommunications
Perigee/Apogee	1477/1533 km
Inclination	74°
Period	116.1 min
Launch vehicle
Launch site	Plesetsk


 Cosmos 0718

General

Designation	07685 / 75016H
Launch date	28 Feb 1975
Country of origin	CIS
Mission	Telecommunications
Perigee/Apogee	1427/1487 km
Inclination	74°
Period	115 min
Launch vehicle
Launch site	Plesetsk


 Cosmos 0732

General

Designation	07820 / 75045A
Launch date	28 May 1975
Country of origin	CIS
Mission	Telecommunications
Perigee/Apogee	1401/1468 km
Inclination	74°
Period	114.6 min
Launch vehicle
Launch site	Plesetsk


 Cosmos 0733

General

Designation	07822 / 75045B
Launch date	28 May 1975
Country of origin	CIS
Mission	Telecommunications
Perigee/Apogee	1467/1552 km
Inclination	74°
Period	116.2 min
Launch vehicle
Launch site	Plesetsk


 Cosmos 0734

General

Designation	07823 / 75045C
Launch date	28 May 1975
Country of origin	CIS
Mission	Telecommunications
Perigee/Apogee	1441/1469 km
Inclination	74°
Period	115 min
Launch vehicle
Launch site	Plesetsk


 Cosmos 0735

General

Designation	07824 / 75045D
Launch date	28 May 1975
Country of origin	CIS
Mission	Telecommunications
Perigee/Apogee	1459/1472 km
Inclination	74°
Period	115.2 min
Launch vehicle
Launch site	Plesetsk


 Cosmos 0736

General

Designation	07825 / 75045E
Launch date	28 May 1975
Country of origin	CIS
Mission	Telecommunications
Perigee/Apogee	1467/1484 km
Inclination	74°
Period	115.5 min
Launch vehicle
Launch site	Plesetsk


 Cosmos 0737

General

Designation	07826 / 75045F
Launch date	28 May 1975
Country of origin	CIS
Mission	Telecommunications
Perigee/Apogee	1468/1484 km
Inclination	74°
Period	115.9 min
Launch vehicle
Launch site	Plesetsk


 Cosmos 0738

General

Designation	07827 / 75045G
Launch date	28 May 1975
Country of origin	CIS
Mission	Telecommunications
Perigee/Apogee	1467/1506 km
Inclination	74°
Period	115.7 min
Launch vehicle
Launch site	Plesetsk


 Cosmos 0739

General

Designation	07828 / 75045H
Launch date	28 May 1975
Country of origin	CIS
Mission	Telecommunications
Perigee/Apogee	1421/1506 km
Inclination	74°
Period	115.7 min
Launch vehicle
Launch site	Plesetsk


 Cosmos 0775

General

Designation	08357 / 75097A
Launch date	8 Oct 1975
Country of origin	CIS
Mission	Military: early warning (Oko GEO, also called Prognoz 1st generation)
Geostationary orbit	25°West
Launch vehicle	Proton #54

First satellite of the Oko series for early warning put on geostationary orbit. It was the same design as the Oko satellites on molnyia type orbit. Four such satellites were launched: Cosmos 0775, Cosmos 1546, Cosmos 1629 and Cosmos1894. The replacement series is called Prognoz 2nd generation.


 Cosmos 0777

General

Designation	08416 / 75102A
Launch date	29 Oct 1975
Country of origin	CIS
Mission
Perigee/Apogee	425/442 km
Inclination	65°
Period	93.9 min
Launch vehicle
Launch site	Tyuratam
End of life

Decay	3 Jun 1976


 Cosmos 0782

General

Designation	08450 / 75110A
Launch date	25 Nov 1975
Country of origin	CIS
Mission	Scientific
Perigee/Apogee	218/384 km
Inclination	62.8°
Period	90.5 min
Launch vehicle
Launch site	Plesetsk

Study of animals and vegetals in space

End of life

Decay	15 Dec 1975


 Cosmos 0936

General

Designation	10172 / 77074A
Launch date	3 Aug 1977
Country of origin	CIS
Mission	Scientific
Perigee/Apogee	219/396 km
Inclination	62.8°
Period	90.6 min
Launch vehicle
Launch site	Plesetsk

Study of animals and vegetals in space

End of life

Decay	22 Aug 1977


 Cosmos 0954

General

Designation	10361 / 77090A
Launch date	18 Sep 1977
Country of origin	CIS
Mission	Military: ocean reconnaissance (Rorsat)
Perigee/Apogee	251/265 km
Inclination	65°
Period	89.7 min
Launch vehicle
Launch site	Tyuratam
End of life

Decay	24 Jan 1978

Decayed in Canada. It was equipped with a 508 kg Romachka nuclear reactor for power supply with 49 kg of uranium. The CIS payed $2.55 million as compensation


 Cosmos 1000

General

Designation	10776 / 78034A
Launch date	31 Mar 1978
Country of origin	CIS
Mission	Navigation (Tsikada)
Perigee/Apogee	954/1006 km
Inclination	82.9°
Period	104.7 min
Launch vehicle
Launch site	Plesetsk


 Cosmos 1094

General

Designation	11333 / 79033A
Launch date	18 Apr 1979
Country of origin	CIS
Mission	Ocean observation
Perigee/Apogee	426/442 km
Inclination	65°
Period	93.3 min
Launch vehicle
Launch site	Tyuratam
End of life

Decay	7 Nov 1979


 Cosmos 1267

Also called TKS Merkur #2

General

Designation	12419 / 81039A
Launch date	15 Apr 1981
Country of origin	CIS
Mission
Perigee/Apogee	192/259 km
Inclination	51.6°
Period	88.9 min
Launch vehicle	Proton #88

First spacecraft to dock with Salyout 6

End of life

Decay	29 Jul 1982


 Cosmos 1366

General

Designation	13177 / 82044A
Launch date	17 May 1982
Country of origin	CIS
Mission	Military: Telecommunications (Geizer)
Geostationary orbit	80°E
Launch vehicle	Proton #97


 Cosmos 1402

General

Designation	13441 / 82084A
Launch date	30 Aug 1982
Country of origin	CIS
Mission	Military: ocean reconnaissance (Rorsat)
Perigee/Apogee	250/266 km
Inclination	65.6°
Period	89.6 min
Launch vehicle
Launch site	Tyuratam

This satellite was powered by a nuclear reactor which separated. The satellite itself decayed in 2 parts on 30 Dec 1982 and 23 Jan 1983 (Indian ocean) Those part were not, or not very radioactive. The nuclear engine decayed on 7 Feb 1983 in the Atlantic.

End of life

Decay	23 Jan 1983


 Cosmos 1443

Also called TKS Merkur #3

General

Designation	13868 / 83013A
Launch date	2 Mar 1983
Country of origin	CIS
Mission
Perigee/Apogee	194/261 km
Inclination	51.6°
Period	89 min
Launch vehicle	Proton #104

First spacecraft to dock with Salyout 7 (10 Mar 1983)

End of life

Decay	19 Sep 1983


 Cosmos 1540

General

Designation	14783 / 84022A
Launch date	2 Mar 1984
Country of origin	CIS
Mission	Military: Telecommunications (Geizer)
Geostationary orbit	141°E
Launch vehicle	Proton #117


 Cosmos 1546

General

Designation	14867 / 84031A
Launch date	29 Mar 1984
Country of origin	CIS
Mission	Military: early warning (Oko GEO, also called Prognoz 1st generation)
Geostationary orbit	24°W
Launch vehicle	Proton #119
End of life

Out of service	yes


 Cosmos 1629

General

Designation	15574 / 85016A
Launch date	21 Feb 1985
Country of origin	CIS
Mission	Military: early warning (Oko GEO, also called Prognoz 1st generation)
Geostationary orbit	24°W
Launch vehicle	Proton #130
End of life

Out of service	yes


 Cosmos 1700

General

Designation	16199 / 85102A
Launch date	25 Oct 1985
Country of origin	CIS
Mission	Military: Telecommunications: Luch
Geostationary orbit	95°E
Launch vehicle	Proton #136
End of life

Out of service	Feb 1995
Cause	replaced by Luch 0
Technical data

Specifications


 Cosmos 1738

General

Designation	16667 / 86027A
Launch date	4 Apr 1986
Country of origin	CIS
Mission	Military: Telecommunications (Geizer)
Geostationary orbit	13.5°W
Launch vehicle	Proton #141
End of life

Out of service	yes, in early 1995?
Technical data

Specifications


 Cosmos 1849

General

Designation	18083 / 87048A
Launch date	4 Jun 1987
Country of origin	CIS
Mission	Military: warning
Perigee/Apogee	3104/37311 km
Inclination	67.1°
Period	719 min
Launch vehicle
Launch site	Plesetsk


 Cosmos 1850

General

Designation	18095 / 87049A
Launch date	9 Jun 1987
Country of origin	CIS
Mission	Telecommunications
Perigee/Apogee	775/798 km
Inclination	74°
Period	100.6 min
Launch vehicle
Launch site	Plesetsk


 Cosmos 1851

General

Designation	18103 / 87050A
Launch date	12 Jun 1987
Country of origin	CIS
Mission	Military: warning
Perigee/Apogee	3671/36713 km
Inclination	65.5°
Period	718.4 min
Launch vehicle
Launch site	Plesetsk


 Cosmos 1852

General

Designation	18113 / 87051A
Launch date	16 Jun 1987
Country of origin	CIS
Mission	Telecommunications
Perigee/Apogee	1471/1497 km
Inclination	74°
Period	115.6 min
Launch vehicle
Launch site	Plesetsk


 Cosmos 1853

General

Designation	18114 / 87051B
Launch date	16 Jun 1987
Country of origin	CIS
Mission	Telecommunications
Perigee/Apogee	1470/1480 km
Inclination	74°
Period	115.4 min
Launch vehicle
Launch site	Plesetsk


 Cosmos 1854

General

Designation	18115 / 87051C
Launch date	16 Jun 1987
Country of origin	CIS
Mission	Telecommunications
Perigee/Apogee	1456/1478 km
Inclination	74°
Period	115.3 min
Launch vehicle
Launch site	Plesetsk


 Cosmos 1855

General

Designation	18116 / 87051D
Launch date	16 Jun 1987
Country of origin	CIS
Mission	Telecommunications
Perigee/Apogee	1444/1475 km
Inclination	74°
Period	115.1 min
Launch vehicle
Launch site	Plesetsk


 Cosmos 1856

General

Designation	18117 / 87051E
Launch date	16 Jun 1987
Country of origin	CIS
Mission	Telecommunications
Perigee/Apogee	1429/1475 km
Inclination	74°
Period	114.9 min
Launch vehicle
Launch site	Plesetsk


 Cosmos 1857

General

Designation	18118 / 87051F
Launch date	16 Jun 1987
Country of origin	CIS
Mission	Telecommunications
Perigee/Apogee	1414/1475 km
Inclination	74°
Period	114.8 min
Launch vehicle
Launch site	Plesetsk


 Cosmos 1858

General

Designation	18119 / 87051G
Launch date	16 Jun 1987
Country of origin	CIS
Mission	Telecommunications
Perigee/Apogee	1399/1476 km
Inclination	74°
Period	114.6 min
Launch vehicle
Launch site	Plesetsk


 Cosmos 1859

General

Designation	18120 / 87051H
Launch date	16 Jun 1987
Country of origin	CIS
Mission	Telecommunications
Perigee/Apogee	1385/1474 km
Inclination	74°
Period	114.4 min
Launch vehicle
Launch site	Plesetsk


 Cosmos 1860

General

Designation	18122 / 87052A
Launch date	18 Jun 1987
Country of origin	CIS
Mission	Military: ocean reconnaissance (Rorsat)
Perigee/Apogee	900/992 km
Inclination	65°
Period	104 min
Launch vehicle
Launch site	Plesetsk

Equipped with a nuclear reactor


 Cosmos 1861

General

Designation	18129 / 87054A
Launch date	23 Jun 1987
Country of origin	CIS
Mission	Navigation (Tsikada)
Perigee/Apogee	996/996 km
Inclination	82.9°
Period	104.9 min
Launch vehicle
Launch site	Plesetsk
Technical data

Plane 12

Radio Sputnik 10

beacon/robot	29.357 Mhz (cw)
beacon/robot	29.403 Mhz (cw)
mode a uplink	145.860 - 145.900 Mhz (ssb,cw)
mode a downlink	29.360 - 29.400 Mhz (ssb,cw)
robot a uplink	145.820 Mhz (cw)
robot a downlink	29.357 or 29.403 Mhz (cw)
beacon/robot	29.357 Mhz (cw)
beacon/robot	29.403 Mhz (cw)
mode k uplink	21.160 - 21.200 Mhz (ssb,cw)
mode k downlink	29.360 - 29.400 Mhz (ssb,cw)
robot k uplink	21.120 Mhz (cw)
robot k downlink	29.357 or 29.403 Mhz (cw)
beacon/robot	145.857 Mhz (cw)
beacon/robot	145.903 Mhz (cw)
mode t uplink	21.160 - 21.200 Mhz (ssb,cw)
mode t downlink	145.860 - 145.900 Mhz (ssb,cw)
robot t uplink	21.120 Mhz (cw)
robot t downlink	145.857 or 145.903 Mhz (cw)
Radio Sputnik 11

beacon/robot	29.407 Mhz (cw)
beacon/robot	29.453 Mhz (cw)
mode a uplink	145.910 - 145.950 Mhz (ssb,cw)
mode a downlink	29.410 - 29.450 Mhz (ssb,cw)
robot a uplink	145.830 Mhz (cw)
robot a downlink	29.407 or 29.453 Mhz (cw)
beacon/robot	29.407 Mhz (cw)
beacon/robot	29.453 Mhz (cw)
mode k uplink	21.210 - 21.250 Mhz (ssb,cw)
mode k downlink	29.410 - 29.450 Mhz (ssb,cw)
robot k uplink	21.130 Mhz (cw)
robot k downlink	29.407 or 29.453 Mhz (cw)
beacon/robot	145.907 Mhz (cw)
beacon/robot	145.953 Mhz (cw)
mode t uplink	21.210 - 21.250 Mhz (ssb,cw)
mode t downlink	145.910 - 145.950 Mhz (ssb,cw)
robot t uplink	21.130 Mhz (cw)
robot t downlink	145.907 or 145.953 Mhz (cw)


 Cosmos 1870

General

Designation	18225 / 87064A
Launch date	25 Jul 1987
Country of origin	CIS
Mission	Remote sensing (Almaz-T #2)
Perigee/Apogee	263/278 km
Inclination	71.9°
Period	89.9 min
Launch vehicle	Proton #154
Mass at launch	15 to 20 t

Satellite developped with the United States, France, Finland and Sweden. The SAR module had a resolution of 15 to 30 meters.

End of life

Decay	29 Jul 1989


 Cosmos 1887

General

Designation	18380 / 87083A
Launch date	29 Sep 1987
Country of origin	CIS
Mission
Perigee/Apogee	214/382 km
Inclination	62.8°
Period	90.5 min
Launch vehicle
Launch site	Plesetsk

On board: 2 macaques, 10 rats and 6 fishes

End of life

Decay	12 Oct 1987


 Cosmos 1888

General

Designation	18384 / 87084A
Launch date	1 Oct 1987
Country of origin	CIS
Mission	Military: telecommunications: Geizer
Geostationary orbit	80°E
Launch vehicle	Proton #156
End of life

Out of service	yes
Technical data

Specifications


 Cosmos 1894

General

Designation	18443 / 87091A
Launch date	28 Oct 1987
Country of origin	CIS
Mission	Military: early warning (Oko GEO, also called Prognoz 1st generation)
Geostationary orbit	24°W
Launch vehicle	Proton #157
End of life

Out of service	yes


 Cosmos 1897

General

Designation	18575 / 87096A
Launch date	26 Nov 1987
Country of origin	CIS
Mission	Military: telecommunications: Luch
Geostationary orbit	95°E
Launch vehicle	Proton #158
End of life

Out of service	yes
Technical data

Specifications


 Cosmos 1923

General

Designation	18931 / 88015A
Launch date	10 Mar 1988
Country of origin	CIS
Mission
Perigee/Apogee	190/302 km
Inclination	72.9°
Period	89.4 min
Launch vehicle
Launch site	Plesetsk
End of life

Decay	22 Mar 1988


 Cosmos 1924

General

Designation	18937 / 88016A
Launch date	11 Mar 1988
Country of origin	CIS
Mission	Telecommunications
Perigee/Apogee	1458/1512 km
Inclination	74°
Period	115.7 min
Launch vehicle
Launch site	Plesetsk


 Cosmos 1925

General

Designation	18938 / 88016B
Launch date	11 Mar 1988
Country of origin	CIS
Mission	Telecommunications
Perigee/Apogee	1457/1495 km
Inclination	74°
Period	115.5 min
Launch vehicle
Launch site	Plesetsk


 Cosmos 1926

General

Designation	18939 / 88016C
Launch date	11 Mar 1988
Country of origin	CIS
Mission	Telecommunications
Perigee/Apogee	1458/1477 km
Inclination	74°
Period	115.3 min
Launch vehicle
Launch site	Plesetsk


 Cosmos 1927

General

Designation	18940 / 88016D
Launch date	11 Mar 1988
Country of origin	CIS
Mission	Telecommunications
Perigee/Apogee	1452/1465 km
Inclination	74°
Period	115.1 min
Launch vehicle
Launch site	Plesetsk


 Cosmos 1928

General

Designation	18941 / 88016E
Launch date	11 Mar 1988
Country of origin	CIS
Mission	Telecommunications
Perigee/Apogee	1442/1459 km
Inclination	74°
Period	114.9 min
Launch vehicle
Launch site	Plesetsk


 Cosmos 1929

General

Designation	18942 / 88016F
Launch date	11 Mar 1988
Country of origin	CIS
Mission	Telecommunications
Perigee/Apogee	1426/1459 km
Inclination	74°
Period	114.7 min
Launch vehicle
Launch site	Plesetsk


 Cosmos 1930

General

Designation	18943 / 88016G
Launch date	11 Mar 1988
Country of origin	CIS
Mission	Telecommunications
Perigee/Apogee	1412/1458 km
Inclination	74°
Period	114.6 min
Launch vehicle
Launch site	Plesetsk


 Cosmos 1931

General

Designation	18944 / 88016H
Launch date	11 Mar 1988
Country of origin	CIS
Mission	Telecommunications
Perigee/Apogee	1395/1459 km
Inclination	74°
Period	114.4 min
Launch vehicle
Launch site	Plesetsk


 Cosmos 1932

General

Designation	18957 / 88019A
Launch date	14 Mar 1988
Country of origin	CIS
Mission	Military: ocean reconnaissance (Rorsat)
Perigee/Apogee	921/1007 km
Inclination	65°
Period	104.4 min
Launch vehicle
Launch site	Tyuratam
End of life

Out of service	20 May 1988

Equipped with a nuclear reactor


 Cosmos 1933

General

Designation	18958 / 88020A
Launch date	15 Mar 1988
Country of origin	CIS
Mission	Military: SIGINT (Tselina)
Perigee/Apogee	605/628 km
Inclination	82.5°
Period	97 min
Launch vehicle
Launch site	Plesetsk


 Cosmos 1934

General

Designation	18985 / 88023A
Launch date	22 Mar 1988
Country of origin	CIS
Mission	Military: Navigation (Parus)
Perigee/Apogee	946/1005 km
Inclination	83°
Period	104.6 min
Launch vehicle
Launch site	Plesetsk
End of life

Out of service	yes


 Cosmos 1935

General

Designation	19011 / 88025A
Launch date	24 Mar 1988
Country of origin	CIS
Mission	Military: reconnaissance
Perigee/Apogee	179/356 km
Inclination	67°
Period	89.5 min
Launch vehicle
Launch site	Plesetsk
End of life

Decay	8 Apr 1988


 Cosmos 1957

General

Designation	19276 / 88057A
Launch date	7 Jul 1988
Country of origin	CIS
Mission	Military: reconnaissance
Perigee/Apogee	179/225 km
Inclination	82.6°
Period	88.5 min
Launch vehicle	Soyouz
Launch site	Plesetsk
End of life

Decay	21 Jul 1988


 Cosmos 1958

General

Designation	19320 / 88060A
Launch date	14 Jul 1988
Country of origin	CIS
Mission	Military:
Perigee/Apogee	360/411 km
Inclination	65.8°
Period	92.3 min
Launch vehicle	Cosmos
Launch site	Plesetsk
End of life

Decay	21 Mar 1969


 Cosmos 1959

General

Designation	19324 / 88062A
Launch date	18 Jul 1988
Country of origin	CIS
Mission	Military: Navigation (Parus)
Perigee/Apogee	952/1002 km
Inclination	83°
Period	104.6 min
Launch vehicle	Cosmos
Launch site	Plesetsk
End of life

Out of service	yes


 Cosmos 1960

General

Designation	19338 / 88065A
Launch date	28 Jul 1988
Country of origin	CIS
Mission	Military
Perigee/Apogee	369/379 km
Inclination	65.8°
Period	92 min
Launch vehicle	Cosmos
Launch site	Plesetsk
End of life

Decay	9 Apr 1990


 Cosmos 1961

General

Designation	19344 / 88066A
Launch date	1 Aug 1988
Country of origin	CIS
Mission	Military: Telecommunications: Geizer
Geostationary orbit	see below
Launch vehicle	Proton #169
Location

Begin	End	Position
L: 1 Aug 1988		13.5°W
End of life

Out of service	before 1995?
Cause
Technical data

Specifications


 Cosmos 1962

General

Designation	19372 / 88068A
Launch date	8 Aug 1988
Country of origin	CIS
Mission	Military: reconnaissance
Perigee/Apogee	205/265 km
Inclination	70°
Period	89.2 min
Launch vehicle	SL 16
Launch site	Tyuratam
End of life

Decay	22 Aug 1988


 Cosmos 1963

General

Designation	19384 / 88070A
Launch date	16 Aug 1988
Country of origin	CIS
Mission	Military: reconnaissance
Perigee/Apogee	176/350 km
Inclination	64.8°
Period	89.8 min
Launch vehicle	Soyouz
Launch site	Plesetsk
End of life

Decay	2 Oct 1988


 Cosmos 1964

General

Designation	19412 / 88072A
Launch date	23 Aug 1988
Country of origin	CIS
Mission	Military: reconnaissance
Perigee/Apogee	206/271 km
Inclination	70°
Period	89.3 min
Launch vehicle	Soyouz
Launch site	Tyuratam
End of life

Decay	7 Sep 1988


 Cosmos 1965

General

Designation	19414 / 88073A
Launch date	23 Aug 1988
Country of origin	CIS
Mission	Military: remote sensing (Priroda)
Perigee/Apogee	179/228 km
Inclination	82.3°
Period	88.6 min
Launch vehicle	Soyouz
Launch site	Plesetsk
End of life

Decay	22 Sep 1988


 Cosmos 1966

General

Designation	19445 / 88076A
Launch date	30 Aug 1988
Country of origin	CIS
Mission	Military: telecommunications (experimental)
Perigee/Apogee	2592/37777 km
Inclination	67.4°
Period	718.1 min
Launch vehicle
Launch site	Plesetsk


 Cosmos 1967

General

Designation	19462 / 88079A
Launch date	6 Sep 1988
Country of origin	CIS
Mission	Military: reconnaissance
Perigee/Apogee	191/380 km
Inclination	72.9°
Period	90.2 min
Launch vehicle	Soyouz
Launch site	Plesetsk
End of life

Decay	15 Sep 1988


 Cosmos 1968

General

Designation	19488 / 88082A
Launch date	9 Sep 1988
Country of origin	CIS
Mission	Military: remote sensing
Perigee/Apogee	177/230 km
Inclination	82.3°
Period	88.6 min
Launch vehicle	Soyouz
Launch site	Plesetsk
End of life

Decay	23 Sep 1988


 Cosmos 1969

General

Designation	19495 / 88084A
Launch date	15 Sep 1988
Country of origin	CIS
Mission	Military: reconnaissance
Perigee/Apogee	165/344 km
Inclination	67.1°
Period	89.6 min
Launch vehicle	Soyouz
Launch site	Plesetsk
End of life

Decay	13 Nov 1988


 Cosmos 1970

General

Designation	19501 / 88085A
Launch date	16 Sep 1988
Country of origin	CIS
Mission	Navigation (Uragan)
Perigee/Apogee	19099/19159 km
Inclination	65.7°
Period	675.7 min
Launch vehicle	Proton #171


 Cosmos 1971

General

Designation	19502 / 88085B
Launch date	16 Sep 1988
Country of origin	CIS
Mission	Navigation (Uragan)
Perigee/Apogee	19099/19159 km
Inclination	65.7°
Period	675.7 km
Launch vehicle	Proton #171


 Cosmos 1972

General

Designation	19503 / 88085C
Launch date	16 Sep 1988
Country of origin	CIS
Mission	Navigation (Uragan)
Perigee/Apogee	19113/19145 km
Inclination	65.7°
Period	675.7 min
Launch vehicle	Proton #171


 Cosmos 1973

General

Designation	19521 / 88088A
Launch date	22 Sep 1988
Country of origin	CIS
Mission	Military: reconnaissance
Perigee/Apogee	192/359 km
Inclination	72.8°
Period	90 min
Launch vehicle	Soyouz
Launch site	Plesetsk
End of life

Decay	10 Oct 1988


 Cosmos 1974

General

Designation	19554 / 88092A
Launch date	3 Oct 1988
Country of origin	CIS
Mission	Military: warning
Perigee/Apogee	3323/37025 km
Inclination	64.7°
Period	717.7 min
Launch vehicle	Plesetsk
Launch site	Molniya


 Cosmos 1975

General

Designation	19573 / 88093A
Launch date	11 Oct 1988
Country of origin	CIS
Mission	Military: SIGINT (Tselina)
Perigee/Apogee	604/634 km
Inclination	82.5°
Period	97.1 min
Launch vehicle	Cyclone
Launch site	Plesetsk


 Cosmos 1976

General

Designation	19582 / 88094A
Launch date	13 Oct 1988
Country of origin	CIS
Mission	Military: reconnaissance
Perigee/Apogee	190/366 km
Inclination	72.9°
Period	90.1 min
Launch vehicle	Soyouz
Launch site	Plesetsk
End of life

Decay	27 Oct 1988


 Cosmos 1977

General

Designation	19608 / 88096A
Launch date	25 Oct 1988
Country of origin	CIS
Mission	Military: reconnaissance
Perigee/Apogee	3263/37085 km
Inclination	64.7°
Period	717.7 min
Launch vehicle	Molniya
Launch site	Plesetsk


 Cosmos 1978

General

Designation	19612 / 88097A
Launch date	27 Oct 1988
Country of origin	CIS
Mission	Military: reconnaissance
Perigee/Apogee	190/364 km
Inclination	72.9°
Period	90.1 min
Launch vehicle	Soyouz
Launch site	Plesetsk
End of life

Decay	10 Nov 1988


 Cosmos 1979

General

Designation	19647 / 88101A
Launch date	18 Nov 1988
Country of origin	CIS
Mission	Military
Perigee/Apogee	402/415 km
Inclination	65°
Period	92.7 min
Launch vehicle
Launch site	Tyuratam
End of life

Decay	25 Dec 1989


 Cosmos 1980

General

Designation	19649 / 88102A
Launch date	23 Nov 1988
Country of origin	CIS
Mission	Military: electronic listening (Elint)
Perigee/Apogee	840/850 km
Inclination	71°
Period	101.8 min
Launch vehicle
Launch site	Tyuratam


 Cosmos 1982

General

Designation	19662 / 88105A
Launch date	30 Nov 1988
Country of origin	CIS
Mission	Military: photography reconnaissance
Perigee/Apogee	204/377 km
Inclination	70°
Period	90.3 min
Launch vehicle	Soyouz
Launch site	Plesetsk
End of life

Decay	14 Dec 1988


 Cosmos 1983

General

Designation	19672 / 88107A
Launch date	8 Dec 1988
Country of origin	CIS
Mission	Military: reconnaissance
Perigee/Apogee	243/256 km
Inclination	62.8°
Period	89.5 min
Launch vehicle	Soyouz
Launch site	Plesetsk
End of life

Decay	22 Dec 1988


 Cosmos 1984

General

Designation	19705 / 88110A
Launch date	16 Dec 1988
Country of origin	CIS
Mission	Military: reconnaissance
Perigee/Apogee	186/323 km
Inclination	62.8°
Period	89.6 min
Launch vehicle	Soyouz
Launch site	Plesetsk
End of life

Decay	13 Feb 1989


 Cosmos 1985

General

Designation	19720 / 88113A
Launch date	23 Dec 1988
Country of origin	CIS
Mission	Military: electronic listening
Perigee/Apogee	206/220 km
Inclination	73.5°
Period	88.8 min
Launch vehicle	Cyclone
Launch site	Plesetsk
End of life

Decay	4 May 1992


 Cosmos 1986

General

Designation	19734 / 88116A
Launch date	29 Dec 1988
Country of origin	CIS
Mission	Military: observation
Perigee/Apogee	193/289 km
Inclination	64.8°
Period	89.3 min
Launch vehicle	Soyouz
Launch site	Tyuratam
End of life

Decay	11 Feb 1989


 Cosmos 1987

Also called Glonass 40

General

Designation	19749 / 89001A
Launch date	10 Jan 1989
Country of origin	CIS
Mission	Navigation (Uragan)
Perigee/Apogee	19113/19145 km
Inclination	64.9°
Period	675.7 min
Launch vehicle	Proton #174
End of life

Out of service	yes


 Cosmos 1988

Also called Glonass 41

General

Designation	19750 / 89001B
Launch date	10 Jan 1989
Country of origin	CIS
Mission	Navigation (Uragan)
Perigee/Apogee	19111/19147 km
Inclination	65°
Period	675.7 min
Launch vehicle	Proton #174
End of life

Out of service	yes


 Cosmos 1989

General

Designation	19751 / 89001C
Launch date	10 Jan 1989
Country of origin	CIS
Mission	Navigation (Etalon #1)
Perigee/Apogee	19097/19152 km
Inclination	64.9°
Period	675.5 min
Launch vehicle	Proton #174


 Cosmos 1990

General

Designation	19756 / 89002A
Launch date	12 Jan 1989
Country of origin	CIS
Mission	Military: remote sensing (Priroda)
Perigee/Apogee	177/227 km
Inclination	82.6°
Period	88.5 min
Launch vehicle	Soyouz
Launch site	Plesetsk
End of life

Decay	11 Feb 1989


 Cosmos 1991

General

Designation	19758 / 89003A
Launch date	18 Jan 1989
Country of origin	CIS
Mission	Military: remote sensing (Priroda)
Perigee/Apogee	204/375 km
Inclination	70°
Period	90.3 min
Launch vehicle	Soyouz
Launch site	Tyuratam
End of life

Decay	1 Feb 1989


 Cosmos 1992

General

Designation	19769 / 89005A
Launch date	26 Jan 1989
Country of origin	CIS
Mission	Telecommunications
Perigee/Apogee	764/798 km
Inclination	74°
Period	100.5 min
Launch vehicle	Soyouz
Launch site	Plesetsk


 Cosmos 1993

General

Designation	19774 / 89007A
Launch date	28 Jan 1989
Country of origin	CIS
Mission	Military: reconnaissance
Perigee/Apogee	171/347 km
Inclination	64.8°
Period	89.7 min
Launch vehicle	Soyouz
Launch site	Tyuratam
End of life

Decay	27 Mar 1989


 Cosmos 1994

General

Designation	19785 / 89009A
Launch date	10 Feb 1989
Country of origin	CIS
Mission	Telecommunications
Perigee/Apogee	1391/1414 km
Inclination	82.6°
Period	113.9 min
Launch vehicle	Tsyclon
Launch site	Plesetsk


 Cosmos 1995

General

Designation	19786 / 89009B
Launch date	10 Feb 1989
Country of origin	CIS
Mission	Telecommunications
Perigee/Apogee	1409/1415 km
Inclination	82.6°
Period	114.1 min
Launch vehicle	Tsyclon
Launch site	Plesetsk


 Cosmos 1996

General

Designation	19787 / 89009C
Launch date	10 Feb 1989
Country of origin	CIS
Mission	Telecommunications
Perigee/Apogee	1403/1414 km
Inclination	82.6°
Period	114 min
Launch vehicle	Tsyclon
Launch site	Plesetsk


 Cosmos 1997

General

Designation	19788 / 89009D
Launch date	10 Feb 1989
Country of origin	CIS
Mission	Telecommunications
Perigee/Apogee	1397/1414 km
Inclination	82.6°
Period	113.9 min
Launch vehicle	Tsyclon
Launch site	Plesetsk


 Cosmos 1998

General

Designation	19789 / 89009E
Launch date	10 Feb 1989
Country of origin	CIS
Mission	Telecommunications
Perigee/Apogee	1387/1414 km
Inclination	82.6°
Period	113.8 min
Launch vehicle	Tsyclon
Launch site	Plesetsk


 Cosmos 1999

General

Designation	19790 / 89009F
Launch date	10 Feb 1989
Country of origin	CIS
Mission	Telecommunications
Perigee/Apogee	1381/1414 km
Inclination	82.6°
Period	113.7 min
Launch vehicle	Tsyclon
Launch site	Plesetsk


 Cosmos 2000

General

Designation	19792 / 89010A
Launch date	10 Feb 1989
Country of origin	CIS
Mission	Military: telecommunications
Perigee/Apogee	175/243 km
Inclination	82.3°
Period	88.7 min
Launch vehicle	Tsyclon
Launch site	Plesetsk
End of life

Decay	2 Mar 1989


 Cosmos 2001

General

Designation	19796 / 89011A
Launch date	14 Feb 1989
Country of origin	CIS
Mission	Military: warning
Perigee/Apogee	2437/37977 km
Inclination	66.5°
Period	719 min
Launch vehicle	Molniya
Launch site	Plesetsk


 Cosmos 2002

General

Designation	19800 / 89012A
Launch date	14 Feb 1989
Country of origin	CIS
Mission	Military: radar calibration
Perigee/Apogee	179/1525 km
Inclination	65.8°
Period	102 min
Launch vehicle	Cosmos
Launch site	Plesetsk
End of life

Decay	15 Oct 1989


 Cosmos 2003

General

Designation	19818 / 89015A
Launch date	17 Feb 1989
Country of origin	CIS
Mission	Military: reconnaissance
Perigee/Apogee	244/255 km
Inclination	62.8°
Period	89.5 min
Launch vehicle	Soyouz
Launch site	Plesetsk
End of life

Decay	3 Mar 1989


 Cosmos 2004

General

Designation	19826 / 89017A
Launch date	22 Feb 1989
Country of origin	CIS
Mission	Navigation
Perigee/Apogee	968/1015 km
Inclination	82.9°
Period	104.9 min
Launch vehicle	Cosmos
Launch site	Plesetsk
Technical data

Downlink frequency: 149.940 MHz


 Cosmos 2005

General

Designation	19862 / 89019A
Launch date	2 Mar 1989
Country of origin	CIS
Mission	Military: reconnaissance
Perigee/Apogee	188/324 km
Inclination	62.8°
Period	89.6 min
Launch vehicle	Soyouz
Launch site	Plesetsk
End of life

Decay	25 Apr 1989


 Cosmos 2006

General

Designation	19893 / 89022A
Launch date	16 Mar 1989
Country of origin	CIS
Mission	Military: observation
Perigee/Apogee	240/380 km
Inclination	62.8°
Period	90.7 min
Launch vehicle	Soyouz
Launch site	Plesetsk
End of life

Decay	31 Mar 1989


 Cosmos 2007

General

Designation	19900 / 89024A
Launch date	23 Mar 1989
Country of origin	CIS
Mission	Military: reconnaissance (5th generation)
Perigee/Apogee	224/262 km
Inclination	64.7°
Period	89.4 min
Launch vehicle	Soyouz
Launch site	Plesetsk
End of life

Decay	22 Sep 1989


 Cosmos 2008

General

Designation	19902 / 89025A
Launch date	24 Mar 1989
Country of origin	CIS
Mission	Telecommunications
Perigee/Apogee	1391/1469 km
Inclination	74°
Period	114.4 min
Launch vehicle	Soyouz
Launch site	Plesetsk


 Cosmos 2009

General

Designation	19903 / 89025B
Launch date	24 Mar 1989
Country of origin	CIS
Mission	Telecommunications
Perigee/Apogee	1406/1470 km
Inclination	74°
Period	114.6 min
Launch vehicle	Soyouz
Launch site	Plesetsk


 Cosmos 2010

General

Designation	19904 / 89025C
Launch date	24 Mar 1989
Country of origin	CIS
Mission	Telecommunications
Perigee/Apogee	1421/1470 km
Inclination	74°
Period	114.8 min
Launch vehicle	Soyouz
Launch site	Plesetsk


 Cosmos 2011

General

Designation	19905 / 89025D
Launch date	24 Mar 1989
Country of origin	CIS
Mission	Telecommunications
Perigee/Apogee	1437/1470 km
Inclination	74°
Period	115 min
Launch vehicle	Soyouz
Launch site	Plesetsk


 Cosmos 2012

General

Designation	19906 / 89025E
Launch date	24 Mar 1989
Country of origin	CIS
Mission	Telecommunications
Perigee/Apogee	1453/1470 km
Inclination	74°
Period	115.1 min
Launch vehicle	Soyouz
Launch site	Plesetsk


 Cosmos 2013

General

Designation	19907 / 89025F
Launch date	24 Mar 1989
Country of origin	CIS
Mission	Telecommunications
Perigee/Apogee	1462/1478 km
Inclination	74°
Period	115.3 min
Launch vehicle	Soyouz
Launch site	Plesetsk


 Cosmos 2014

General

Designation	19908 / 89025G
Launch date	24 Mar 1989
Country of origin	CIS
Mission	Telecommunications
Perigee/Apogee	1469/1487 km
Inclination	74°
Period	115.5 min
Launch vehicle	Soyouz
Launch site	Plestesk


 Cosmos 2015

General

Designation	19909 / 89025H
Launch date	24 Mar 1989
Country of origin	CIS
Mission	Telecommunications
Perigee/Apogee	1467/1507 km
Inclination	74°
Period	115.7 min
Launch vehicle	Soyouz
Launch site	Plesetsk


 Cosmos 2016

General

Designation	19921 / 89028A
Launch date	4 Apr 1989
Country of origin	CIS
Mission	Navigation
Perigee/Apogee	952/1010 km
Inclination	83°
Period	104.7 min
Launch vehicle	Cosmos
Launch site	Plesetsk


 Cosmos 2017

General

Designation	19923 / 89029A
Launch date	6 Apr 1989
Country of origin	CIS
Mission	Military: reconnaissance
Perigee/Apogee	244/260 km
Inclination	62.8°
Period	89.6 min
Launch vehicle	Soyouz
Launch site	Plesetsk
End of life

Decay	19 Apr 1989


 Cosmos 2018

General

Designation	19938 / 89031A
Launch date	20 Apr 1989
Country of origin	CIS
Mission	Military: Navigation (Tsigal)
Perigee/Apogee	185/327 km
Inclination	62.9°
Period	89.6 min
Launch vehicle	Cosmos
Launch site	Plesetsk
End of life

Decay	19 Jun 1989


 Cosmos 2019

General

Designation	19972 / 89034A
Launch date	5 May 1989
Country of origin	CIS
Mission	Military: observation
Perigee/Apogee	241/256 km
Inclination	62.9°
Period	89.5 min
Launch vehicle	Soyouz
Launch site	Plesetsk
End of life

Decay	18 May 1989


 Cosmos 2020

General

Designation	19986 / 89036A
Launch date	17 May 1989
Country of origin	CIS
Mission	Military: reconnaissance
Perigee/Apogee	178/280 km
Inclination	64.8°
Period	89.7 min
Launch vehicle	Soyouz
Launch site	Plesetsk
End of life

Decay	15 Jul 1989


 Cosmos 2021

General

Designation	20000 / 89037A
Launch date	24 May 1989
Country of origin	CIS
Mission	Military: reconnaissance
Perigee/Apogee	204/280 km
Inclination	69.9°
Period	89.4 min
Launch vehicle	Soyouz
Launch site	Plesetsk
End of life

Decay	6 Jul 1989


 Cosmos 2022

Also called Glonass 42

General

Designation	20024 / 89039A
Launch date	31 May 1989
Country of origin	CIS
Mission	Navigation (Uragan)
Perigee/Apogee	19119/19139 km
Inclination	65.5°
Period	675.7 min
Launch vehicle	Proton #177
End of life

Out of service	yes


 Cosmos 2023

Also called Glonass 43

General

Designation	20025 / 89039b
Launch date	31 May 1989
Country of origin	CIS
Mission	Navigation (Uragan)
Perigee/Apogee	19087/19170 km
Inclination	65.5°
Period	675.7 min
Launch vehicle	Proton #177
End of life

Out of service	yes


 Cosmos 2024

General

Designation	20026 / 89039C
Launch date	31 May 1989
Country of origin	CIS
Mission	Military: geodesy (Etalon #2)
Perigee/Apogee	19095/19146 km
Inclination	65.5°
Period	675.4 min
Launch vehicle	Proton #177


 Cosmos 2025

General

Designation	20035 / 89040A
Launch date	1 Jun 1989
Country of origin	CIS
Mission	Military: reconnaissance
Perigee/Apogee	236/256 km
Inclination	62.8°
Period	89.4 min
Launch vehicle	Soyouz
Launch site	Plesetsk
End of life

Decay	15 Jun 1989


 Cosmos 2026

General

Designation	20045 / 89042A
Launch date	7 Jun 1989
Country of origin	CIS
Mission	Navigation
Perigee/Apogee	948/1006 km
Inclination	82.9°
Period	104.6 min
Launch vehicle	Cosmos
Launch site	Plesetsk
Technical data

Downlink frequency: 149.97 MHz


 Cosmos 2027

General

Designation	20064 / 89045A
Launch date	14 Jun 1989
Country of origin	CIS
Mission	Military: radar calibration
Perigee/Apogee	394/427 km
Inclination	65.8°
Period	92.8 min
Launch vehicle	Cosmos
Launch site	Plesetsk
End of life

Decay	14 Apr 1992


 Cosmos 2028

General

Designation	20073 / 89047A
Launch date	16 Jun 1989
Country of origin	CIS
Mission	Military: reconnaissance
Perigee/Apogee	204/243 km
Inclination	70°
Period	89 min
Launch vehicle	Soyouz
Launch site	Plesetsk
End of life

Decay	6 Jul 1989


 Cosmos 2029

General

Designation	20105 / 89051A
Launch date	5 Jul 1989
Country of origin	CIS
Mission	Military: reconnaissance
Perigee/Apogee	178/238 km
Inclination	82.3°
Period	88.7 min
Launch vehicle	Soyouz
Launch site	Plesetsk
End of life

Decay	19 Jul 1989


 Cosmos 2030

General

Designation	20124 / 89054A
Launch date	12 Jul 1989
Country of origin	CIS
Mission	Military: reconnaissance
Perigee/Apogee	162/349 km
Inclination	67.2°
Period	89.6 min
Launch vehicle
Launch site	Plesetsk
End of life

Decay	29 Jul 1989


 Cosmos 2031

General

Designation	20136 / 89056A
Launch date	18 Jul 1989
Country of origin	CIS
Mission	Military
Perigee/Apogee	211/264 km
Inclination	50.4°
Period	89.6 min
Launch vehicle	Soyouz
Launch site	Tyuratam
End of life

Decay	15 Sep 1989


 Cosmos 2032

General

Designation	20145 / 89057A
Launch date	20 Jul 1989
Country of origin	CIS
Mission	Military: reconnaissance
Perigee/Apogee	179/241 km
Inclination	82.3°
Period	88.7 min
Launch vehicle	Soyouz
Launch site	Plesetsk
End of life

Decay	3 Aug 1989


 Cosmos 2033

General

Designation	20147 / 89058A
Launch date	24 Jul 1989
Country of origin	CIS
Mission	Military
Perigee/Apogee	196/322 km
Inclination	65°
Period	89.7 min
Launch vehicle	Zenith (derived from SL 16)
Launch site	Tyuratam
End of life

Decay	6 Jan 1991


 Cosmos 2034

General

Designation	20149 / 89059A
Launch date	25 Jul 1989
Country of origin	CIS
Mission	Navigation
Perigee/Apogee	962/1010 km
Inclination	82.9°
Period	104.8 min
Launch vehicle	Cosmos
Launch site	Plesetsk


 Cosmos 2035

General

Designation	20151 / 89060A
Launch date	2 Aug 1989
Country of origin	CIS
Mission	Military: observation
Perigee/Apogee	176/306 km
Inclination	82.6°
Period	88.6 min
Launch vehicle	Soyouz
Launch site	Plesetsk
End of life

Decay	16 Aug 1989


 Cosmos 2036

General

Designation	20188 / 89065A
Launch date	22 Aug 1989
Country of origin	CIS
Mission	Military: reconnaissance
Perigee/Apogee	244/259 km
Inclination	62.8°
Period	89.5 min
Launch vehicle	Soyouz
Launch site	Plesetsk
End of life

Decay	5 Sep 1989


 Cosmos 2037

General

Designation	20196 / 89068A
Launch date	28 Aug 1989
Country of origin	CIS
Mission	Scientific: geodesy
Perigee/Apogee	1482/1522 km
Inclination	73.6°
Period	116 min
Launch vehicle	Tsyclon
Launch site	Plesetsk


 Cosmos 2038

General

Designation	20232 / 89074A
Launch date	14 Sep 1989
Country of origin	CIS
Mission	Telecommunications
Perigee/Apogee	1389/1408 km
Inclination	82.6°
Period	113.8 min
Launch vehicle	Tsyclon
Launch site	Plesetsk


 Cosmos 2039

General

Designation	20233 / 89074B
Launch date	14 Sep 1989
Country of origin	CIS
Mission	Telecommunications
Perigee/Apogee	1382/1408 km
Inclination	82.6°
Period	113.7 min
Launch vehicle	Tsyclon
Launch site	Plesetsk


 Cosmos 2040

General

Designation	20234 / 89074C
Launch date	14 Sep 1989
Country of origin	CIS
Mission	Telecommunications
Perigee/Apogee	1407/1413 km
Inclination	82.6°
Period	114 min
Launch vehicle	Tsyclon
Launch site	Plesetsk


 Cosmos 2041

General

Designation	20235 / 89074D
Launch date	14 Sep 1989
Country of origin	CIS
Mission	Telecommunications
Perigee/Apogee	1394/1408 km
Inclination	82.6°
Period	113.8 min
Launch vehicle	Tsyclon
Launch site	Plesetsk


 Cosmos 2042

General

Designation	20236 / 89074E
Launch date	14 Sep 1989
Country of origin	CIS
Mission	Telecommunications
Perigee/Apogee	1398/1409 km
Inclination	82.6°
Period	113.9 min
Launch vehicle	Tsyclon
Launch site	Plesetsk


 Cosmos 2043

General

Designation	20237 / 89074F
Launch date	14 Sep 1989
Country of origin	CIS
Mission	Telecommunications
Perigee/Apogee	1406/1407 km
Inclination	82.6°
Period	113.9 min
Launch vehicle	Tsyclon
Launch site	Plesetsk


 Cosmos 2044

Also called BioCosmos 9 or Bion 9

General

Designation	20242 / 89075A
Launch date	15 Sep 1989
Country of origin	CIS
Mission	Scientific
Perigee/Apogee	203/264 km
Inclination	82.3°
Period	89.2 min
Launch vehicle	Soyouz
Launch site	Plesetsk

Satellite with German, Austrian, Canadian, Danish, Spanish, American, French, Hungarian, Norwegian, Rumanian, Swiss and Czech experiments.

End of life

Decay	29 Sep 1989


 Cosmos 2045

General

Designation	20244 / 89076A
Launch date	22 Sep 1989
Country of origin	CIS
Mission	Military: observation
Perigee/Apogee	205/295 km
Inclination	70°
Period	89.5 min
Launch vehicle	Zenith
Launch site	Tyuratam
End of life

Decay	2 Oct 1989


 Cosmos 2047

General

Designation	20279 / 89082A
Launch date	3 Oct 1989
Country of origin	CIS
Mission	Military: reconnaissance
Perigee/Apogee	165/330 km
Inclination	67.1°
Period	89.5 min
Launch vehicle	Zenith
Launch site	Plesetsk
End of life

Decay	21 Nov 1989


 Cosmos 2048

General

Designation	20292 / 89083A
Launch date	17 Oct 1989
Country of origin	CIS
Mission	Military: reconnaissance
Perigee/Apogee	253/269 km
Inclination	62.6°
Period	89.7 min
Launch vehicle	Soyouz
Launch site	Plesetsk
End of life

Decay	26 Oct 1989


 Cosmos 2049

General

Designation	20320 / 89088A
Launch date	17 Nov 1989
Country of origin	CIS
Mission	Military: reconnaissance (5th generation)
Perigee/Apogee	232/251 km
Inclination	64.8°
Period	89.3 min
Launch vehicle	Soyouz
Launch site	Tyuratam
End of life

Decay	19 Jun 1990


 Cosmos 2050

General

Designation	20330 / 89091A
Launch date	23 Nov 1989
Country of origin	CIS
Mission	Military: warning
Perigee/Apogee	2273/38112 km
Inclination	62.7°
Period	718.4 min
Launch vehicle	Molniya
Launch site	Plesetsk


 Cosmos 2051

General

Designation	20334 / 89092A
Launch date	24 Nov 1989
Country of origin	CIS
Mission	Military
Perigee/Apogee	293/310 km
Inclination	64.9°
Period	90.6 min
Launch vehicle
Launch site	Tyuratam
End of life

Decay	21 Jan 1990


 Cosmos 2052

General

Designation	20350 / 89095A
Launch date	30 Nov 1989
Country of origin	CIS
Mission	Military: reconnaissance
Perigee/Apogee	174/320 km
Inclination	67.1°
Period	89.5 min
Launch vehicle
Launch site	Plesetsk
End of life

Decay	24 Jan 1990


 Cosmos 2054

General

Designation	20391 / 89101A
Launch date	27 Dec 1989
Country of origin	CIS
Mission	Military: Telecommunications: Luch
Geostationary orbit	16°W, inclined
Launch vehicle
Launch site	Tyuratam
Technical data

Specifications


 Cosmos 2055

General

Designation	20426 / 90003A
Launch date	17 Jan 1990
Country of origin	CIS
Mission	Military: reconnaissance
Perigee/Apogee	248/260 km
Inclination	62.8°
Period	89.6 min
Launch vehicle	Soyouz
Launch site	Plesetsk
End of life

Decay	29 Jan 1990


 Cosmos 2056

General

Designation	20432 / 90004A
Launch date	18 Jan 1990
Country of origin	CIS
Mission	Military: telecommunications
Perigee/Apogee	769/802 km
Inclination	74°
Period	100.6 min
Launch vehicle	Cosmos
Launch site	Plesetsk


 Cosmos 2057

General

Designation	20457 / 90009A
Launch date	25 Jan 1990
Country of origin	CIS
Mission	Military: reconnaissance
Perigee/Apogee	183/330 km
Inclination	62.8°
Period	89.6 min
Launch vehicle
Launch site	Plesetsk
End of life

Decay	19 Mar 1990


 Cosmos 2058

General

Designation	20465 / 90010A
Launch date	30 Jan 1989
Country of origin	CIS
Mission	Military: SIGINT (Tselina)
Perigee/Apogee	616/645 km
Inclination	82.5°
Period	97.3 min
Launch vehicle
Launch site	Plesetsk


 Cosmos 2059

General

Designation	20476 / 90012A
Launch date	6 Feb 1990
Country of origin	CIS
Mission	Military: radar calibration
Perigee/Apogee	184/1585 km
Inclination	65.8°
Period	102.7 min
Launch vehicle	Cosmos
Launch site	Plesetsk
End of life

Decay	12 Nov 1990


 Cosmos 2061

General

Designation	20527 / 90023A
Launch date	20 Mar 1990
Country of origin	CIS
Mission	Navigation
Perigee/Apogee	967/1015 km
Inclination	82.9°
Period	104.9 min
Launch vehicle	Cosmos
Launch site	Plesetsk


 Cosmos 2062

General

Designation	20529 / 90024A
Launch date	22 Mar 1990
Country of origin	CIS
Mission	Military: reconnaissance
Perigee/Apogee	178/221 km
Inclination	82.3°
Period	88.5 min
Launch vehicle	Soyouz
Launch site	Plesetsk
End of life

Decay	5 Apr 1990


 Cosmos 2063

General

Designation	20536 / 90026A
Launch date	27 Mar 1990
Country of origin	CIS
Mission	Military: early warning (Oko)
Perigee/Apogee	1706/38633 km
Inclination	63.8°
Period	717.5 min
Launch vehicle	Molniya
Launch site	Plesetsk


 Cosmos 2064

General

Designation	20549 / 90029A
Launch date	6 Apr 1990
Country of origin	CIS
Mission	Telecommunications
Perigee/Apogee	1460/1488 km
Inclination	74°
Period	115.4 min
Launch vehicle	Cosmos
Launch site	Plesetsk


 Cosmos 2065

General

Designation	20550 / 90029B
Launch date	6 Apr 1990
Country of origin	CIS
Mission	Telecommunications
Perigee/Apogee	1459/1473 km
Inclination	74°
Period	115.2 min
Launch vehicle	Cosmos
Launch site	Plesetsk


 Cosmos 2066

General

Designation	20551 / 90029C
Launch date	6 Apr 1990
Country of origin	CIS
Mission	Telecommunications
Perigee/Apogee	1383/1461 km
Inclination	74°
Period	114.3 min
Launch vehicle	Cosmos
Launch site	Plesetsk


 Cosmos 2067

General

Designation	20552 / 90029D
Launch date	6 Apr 1990
Country of origin	CIS
Mission	Telecommunications
Perigee/Apogee	1398/1461 km
Inclination	74°
Period	114.4 min
Launch vehicle	Cosmos
Launch site	Plesetsk


 Cosmos 2068

General

Designation	20553 / 90029E
Launch date	6 Apr 1990
Country of origin	CIS
Mission	Telecommunications
Perigee/Apogee	1413/1460 km
Inclination	74°
Period	114.6 min
Launch vehicle	Cosmos
Launch site	Plesetsk


 Cosmos 2069

General

Designation	20554 / 90029F
Launch date	6 Apr 1990
Country of origin	CIS
Mission	Telecommunications
Perigee/Apogee	1427/1461 km
Inclination	74°
Period	114.8 min
Launch vehicle	Cosmos
Launch site	Plesetsk


 Cosmos 2070

General

Designation	20555 / 90029G
Launch date	6 Apr 1990
Country of origin	CIS
Mission	Telecommunications
Perigee/Apogee	1441/1461 km
Inclination	74°
Period	114.9 min
Launch vehicle	Cosmos
Launch site	Plesetsk


 Cosmos 2071

General

Designation	20556 / 90029H
Launch date	6 Apr 1990
Country of origin	CIS
Mission	Telecommunications
Perigee/Apogee	1457/1461 km
Inclination	74°
Period	115.1 min
Launch vehicle	Cosmos
Launch site	Plesetsk


 Cosmos 2072

General

Designation	20568 / 90033A
Launch date	13 Apr 1990
Country of origin	CIS
Mission	Military: reconnaissance (5th generation)
Perigee/Apogee	232/270 km
Inclination	64.7°
Period	89.5 min
Launch vehicle	Soyouz
Launch site	Plesetsk
End of life

Decay	22 Nov 1990


 Cosmos 2073

General

Designation	20573 / 90035A
Launch date	17 Apr 1990
Country of origin	CIS
Mission	Military: reconnaissance
Perigee/Apogee	173/239 km
Inclination	82.4°
Period	88.6 min
Launch vehicle	Soyouz
Launch site	Plesetsk
End of life

Decay	28 Apr 1990


 Cosmos 2074

General

Designation	20577 / 90036A
Launch date	13 Apr 1990
Country of origin	CIS
Mission	Navigation
Perigee/Apogee	962/1002 km
Inclination	82.9°
Period	104.7 min
Launch vehicle	Soyouz
Launch site	Tyuratam
Technical data

Downlink frequencies: 149.910 & 399.760 MHz


 Cosmos 2079

Also called Glonass 44

General

Designation	20619 / 90045A
Launch date	19 May 1990
Country of origin	CIS
Mission	Navigation (Uragan)
Perigee/Apogee	19069/19189 km
Inclination	65.3°
Period	675.7 min
Launch vehicle
Launch site
End of life

Out of service	yes


 Cosmos 2080

Also called Glonass 45

General

Designation	20620 / 90045B
Launch date	19 May 1990
Country of origin	CIS
Mission	Navigation (Uragan)
Perigee/Apogee	19107/19151 km
Inclination	65.3°
Period	675.7 min
Launch vehicle
Launch site
End of life

Out of service	yes


 Cosmos 2081

Also called Glonass 46

General

Designation	20621 / 90045C
Launch date	19 May 1990
Country of origin	CIS
Mission	Navigation (Uragan)
Perigee/Apogee	19107/19151 km
Inclination	65.3°
Period	675.7 min
Launch vehicle
Launch site
End of life

Out of service	yes


 Cosmos 2085

General

Designation	20693 / 90061A
Launch date	18 Jul 1990
Country of origin	CIS
Mission	Military: telecommunications: Geizer
Geostationary orbit	see below
Launch vehicle
Launch site	Tyuratam
Location

Begin	End	Position
L: 18 Jul 1990
Oct 1995		70°E, inclined
Technical data

Specifications


 Cosmos 2100

General

Designation	20804 / 90083A
Launch date	14 Sep 1990
Country of origin	CIS
Mission
Perigee/Apogee	957/1010 km
Inclination	82,9°
Period	104.8 min
Launch vehicle
Launch site	Plesetsk
Technical data

Downlink frequency: 149.970 MHz


 Cosmos 2107

General

Designation	20985 / 90108A
Launch date	4 Dec 1990
Country of origin	CIS
Mission	Military: ocean reconnaissance (Eorsat)
Perigee/Apogee	402/416 km
Inclination	65°
Period	92.8 min
Launch vehicle
Launch site	Plesetsk
End of life

Decay	6 Apr 1992


 Cosmos 2108

General

Designation	21000 / 90109A
Launch date	4 Dec 1990
Country of origin	CIS
Mission	Military: reconnaissance
Perigee/Apogee	164/289 km
Inclination	62.8°
Period	89 min
Launch vehicle	Soyouz
Launch site	Plesetsk
End of life

Decay	28 Jan 1991


 Cosmos 2109

Also called Glonass 47

General

Designation	21006 / 90110A
Launch date	8 Dec 1990
Country of origin	CIS
Mission	Navigation (Uragan)
Perigee/Apogee	18975/19283 km
Inclination	64.9°
Period	675.7 min
Launch vehicle	Proton #193
End of life

Out of service	yes


 Cosmos 2110

Also called Glonass 48

General

Designation	21007 / 90110B
Launch date	8 Dec 1990
Country of origin	CIS
Mission	Navigation (Uragan)
Perigee/Apogee	19036/19223 km
Inclination	64.9°
Period	675.7 min
Launch vehicle	Proton #193
End of life

Out of service	yes


 Cosmos 2111

Also called Glonass 49 or Glonass 249

General

Designation	21008 / 90110C
Launch date	8 Dec 1990
Country of origin	CIS
Mission	Navigation (Uragan)
Perigee/Apogee	19110/19148 km
Inclination	65°
Period	675.7 min
Launch vehicle	Proton #193
Technical data

Frequency (MHz)	L1 = 1602 + 0.5625 * channel L2 = 1246 + 0.4375 * channel
Channel	23
Plane	1
Slot	5


 Cosmos 2112

General

Designation	21014 / 90111A
Launch date	10 Dec 1990
Country of origin	CIS
Mission	Telecommunications
Perigee/Apogee	765/807 km
Inclination	74°
Period	100.6 min
Launch vehicle
Launch site	Plesetsk


 Cosmos 2123

General

Designation	21089 / 91007A
Launch date	5 Feb 1991
Country of origin	CIS
Mission	Navigation (Tsikada)
Perigee/Apogee	961/1003 km
Inclination	82.9°
Period	104.7 min
Launch vehicle
Launch site	Plesetsk
Technical data

Downlink frequencies (navigation payload): 150 & 400 MHz

Plane 13

Radio Sputnik 12

beacon/robot	29.408 mhz (cw)
beacon/robot	29.454 mhz (cw)
mode a uplink	145.910 - 145.950 mhz (ssb,cw)
mode a downlink	29.410 - 29.450 mhz (ssb,cw)
robot a uplink	145.831 mhz (cw)
robot a downlink	29.408 or 29.454 mhz (cw)
beacon/robot	29.408 mhz (cw)
beacon/robot	29.454 mhz (cw)
mode k uplink	21.210 - 21.250 mhz (ssb,cw)
mode k downlink	29.410 - 29.450 mhz (ssb,cw)
robot k uplink	21.129 mhz (cw)
robot k downlink	29.408 or 29.454 mhz (cw)
beacon/robot	145.912 mhz (cw)
beacon/robot	145.959 mhz (cw)
mode t uplink	21.210 - 21.250 hz (ssb,cw)
mode t downlink	145.910 - 145.950 mhz (ssb,cw)
robot t uplink	21.129 mhz (cw)
robot t downlink	145.912 or 145.959 mhz (cw)
Radio Sputnik 13

beacon/robot	29.458 mhz (cw)
beacon/robot	29.504 mhz (cw)
mode a uplink	145.960 - 146.000 mhz (ssb,cw)
mode a downlink	29.460 - 29.500 mhz (ssb,cw)
robot a uplink	145.840 mhz (cw)
robot a downlink	29.458 or 29.504 mhz (cw)
beacon/robot	29.458 mhz (cw)
beacon/robot	29.504 mhz (cw)
mode k uplink	21.260 - 21.300 mhz (ssb,cw)
mode k downlink	29.460 - 29.500 mhz (ssb,cw)
robot k uplink	21.138 mhz (cw)
robot k downlink	29.458 or 29.504 mhz (cw)
beacon/robot	145.862 mhz (cw)
beacon/robot	145.908 mhz (cw)
mode t uplink	21.260 - 21.300 mhz (ssb,cw)
mode t downlink	145.960 - 146.000 mhz (ssb,cw)
robot t uplink	21.138 mhz (cw)
robot downlink	145.862 or 145.908 mhz (cw)


 Cosmos 2133

General

Designation	21111 / 91010A
Launch date	14 Feb 1991
Country of origin	CIS
Mission	Military: early warning (Prognoz 2nd generation)
Geostationary orbit	80°E, inclined
Launch vehicle
Launch site	Tyuratam
Technical data

Specifications

Prime contractor	NPO Lavochkin
Platform
Mass at launch	2600 kg
Mass in orbit
Length
Width
Height
Stabilization
DC power
Design lifetime

S-band capacity


 Cosmos 2139

Also called Glonass 50

General

Designation	21216 / 91025A
Launch date	4 Apr 1991
Country of origin	CIS
Mission	Navigation (Uragan)
Perigee/Apogee	19103/19155 km
Inclination	65.1°
Period	675.7 min
Launch vehicle
Launch site
End of life

Out of service	yes


 Cosmos 2140

Also called Glonass 51

General

Designation	21217 / 91025B
Launch date	4 Apr 1991
Country of origin	CIS
Mission	Navigation (Uragan)
Perigee/Apogee	19102/19156 km
Inclination	65.1°
Period	675.7 min
Launch vehicle
Launch site
End of life

Out of service	yes


 Cosmos 2141

Also called Glonass 52

General

Designation	21218 / 91025C
Launch date	4 Apr 1991
Country of origin	CIS
Mission	Navigation (Uragan)
Perigee/Apogee	19109/19149 km
Inclination	65.1°
Period	675.7 min
Launch vehicle
Launch site
End of life

Out of service	yes


 Cosmos 2142

General

Designation	21230 / 91029A
Launch date	16 Apr 1991
Country of origin	CIS
Mission
Perigee/Apogee	958/1017 km
Inclination	83°
Period	104.9 min
Launch vehicle
Launch site	Plesetsk
Technical data

Downlink frequencies: 150.030 & 400.080 MHz


 Cosmos 2155

General

Designation	21702 / 91064A
Launch date	13 Sep 1991
Country of origin	CIS
Mission	Military: early warning
Geostationary orbit
Launch vehicle
Launch site	Tyuratam


 Cosmos 2172

General

Designation	21789 / 91079A
Launch date	22 Nov 1991
Country of origin	CIS
Mission	Military: telecommunications: Geizer
Geostationary orbit	13.5°W, inclined
Launch vehicle
Launch site	Tyuratam
Technical data

Specifications


 Cosmos 2173

General

Designation	21796 / 91081A
Launch date	26 Nov 1991
Country of origin	CIS
Mission	Military: Navigation (Parus)
Perigee/Apogee	944/1015 km
Inclination	82.9°
Period	104.7 min
Launch vehicle
Launch site
End of life

Out of service	yes
Technical data

Downlink frequency: 149.97 & 399.92 MHz

Plane 4


 Cosmos 2177

Also called Glonass 53

General

Designation	21853 / 92005A
Launch date	29 Jan 1992
Country of origin	CIS
Mission	Navigation (Uragan)
Perigee/Apogee	19112/19146 km
Inclination	64.8°
Period	675.7 min
Launch vehicle
Launch site
End of life

Out of service	yes


 Cosmos 2178

Also called Glonass 54 or Glonass 769

General

Designation	21854 / 92005B
Launch date	29 Jan 1992
Country of origin	CIS
Mission	Navigation (Uragan)
Perigee/Apogee	19088/19170 km
Inclination	65°
Period	675.7 min
Launch vehicle
Launch site
Technical data

Frequency (MHz)	L1 = 1602 + 0.5625 * channel L2 = 1246 + 0.4375 * channel
Channel	2
Plane	1
Slot	8


 Cosmos 2179

Also called Glonass 55 or Glonass 771

General

Designation	21855 / 92005C
Launch date	29 Jan 1992
Country of origin	CIS
Mission	Navigation (Uragan)
Perigee/Apogee	19109/19149 km
Inclination	65°
Period	675.7 min
Launch vehicle
Launch site
Technical data

Frequency (MHz)	L1 = 1602 + 0.5625 * channel L2 = 1246 + 0.4375 * channel
Channel	23
Plane	1
Slot	1


 Cosmos 2204

Also called Glonass 56 or Glonass 774

General

Designation	22056 / 92047A
Launch date	30 Jul 1992
Country of origin	CIS
Mission	Navigation (Uragan)
Perigee/Apogee	19114/19144 km
Inclination	64°
Period	675.7 min
Launch vehicle
Launch site
Technical data

Frequency (MHz)	L1 = 1602 + 0.5625 * channel L2 = 1246 + 0.4375 * channel
Channel	1
Plane	3
Slot	24


 Cosmos 2205

Also called Glonass 57 or Glonass 756

General

Designation	22057 / 92047B
Launch date	30 Jul 1992
Country of origin	CIS
Mission	Navigation (Uragan)
Perigee/Apogee	19110/19148 km
Inclination	64°
Period	675.7 min
Launch vehicle
Launch site
Technical data

Frequency (MHz)	L1 = 1602 + 0.5625 * channel L2 = 1246 + 0.4375 * channel
Channel	24
Plane	3
Slot	21


 Cosmos 2206

Also called Glonass 58 or Glonass 772

General

Designation	22058 / 92047C
Launch date	30 Jul 1992
Country of origin	CIS
Mission	Navigation (Uragan)
Perigee/Apogee	19098/19160 km
Inclination	64°
Period	675.7 min
Launch vehicle
Launch site
End of life

Out of service	27 Aug 1994


 Cosmos 2209

General

Designation	22112 / 92059A
Launch date	10 Sep 1992
Country of origin	CIS
Mission	Military: early warning (Prognoz 2nd generation)
Geostationary orbit	24°W, inclined
Launch vehicle
Launch site	Tyuratam
Technical data

Specifications

Prime contractor	NPO Lavochkin
Platform
Mass at launch	2600 kg
Mass in orbit
Length
Width
Height
Stabilization
DC power
Design lifetime

S-band capacity


 Cosmos 2218

General

Designation	22207 / 92073A
Launch date	29 Oct 1992
Country of origin	CIS
Mission	Military: Navigation (Parus)
Perigee/Apogee	963/1013 km
Inclination	82.9°
Period	104.9 min
Launch vehicle
Launch site
Technical data

Downlink frequency: 149.940 & 399.840 MHz

Plane 3


 Cosmos 2219

General

Designation	22219 / 92076A
Launch date	17 Nov 1992
Country of origin	CIS
Mission	Earth observation
Perigee/Apogee	843/855 km
Inclination	71°
Period	101.9 min
Launch vehicle	Zenith
Launch site	Tyuratam


 Cosmos 2220

General

Designation	22226 / 92077A
Launch date	20 Nov 1992
Country of origin	CIS
Mission	Military
Perigee/Apogee	164/341 km
Inclination	67.2°
Period	89.6 min
Launch vehicle	Soyouz
Launch site	Plesetsk
End of life

Decay	18 Jan 1993


 Cosmos 2221

General

Designation	22236 / 92080A
Launch date	24 Nov 1992
Country of origin	CIS
Mission	Military: SIGINT (Tselina)
Perigee/Apogee	629/662 km
Inclination	82.5°
Period	97.6 min
Launch vehicle	Tsyclon
Launch site	Plesetsk


 Cosmos 2222

General

Designation	22238 / 92081A
Launch date	25 Nov 1992
Country of origin	CIS
Mission	Military: early warning (Oko)
Perigee/Apogee	1172/39195 km
Inclination	62.9°
Period	718.1 min
Launch vehicle	Molniya
Launch site	Plesetsk


 Cosmos 2223

General

Designation	22260 / 92087A
Launch date	9 Dec 1992
Country of origin	CIS
Mission	Reconnaissance (5th generation)
Perigee/Apogee	238/271 km
Inclination	64.6°
Period	89.6 min
Launch vehicle	Soyouz
Launch site	Tyuratam
End of life

Decay	16 Dec 1993


 Cosmos 2224

General

Designation	22269 / 92088A
Launch date	17 Dec 1992
Country of origin	CIS
Mission	Military: early warning (Prognoz 2nd generation)
Geostationary orbit	12°E, inclined
Launch vehicle
Launch site	Tyuratam
Mass at launch	2600 kg

Built by NPO Lavochkin. S-band capacity


 Cosmos 2230

General

Designation	22307 / 93001A
Launch date	12 Jan 1993
Country of origin	CIS
Mission	Navigation (Tsikada)
Perigee/Apogee	968/1005 km
Inclination	82.9°
Period	104.8 min
Launch vehicle	Cosmos
Launch site	Plesetsk

Built by PO Polyot

Technical data

Downlink frequency: 150 & 400 MHz

Plane 11?


 Cosmos 2231

General

Designation	22317 / 93004A
Launch date	19 Jan 1993
Country of origin	CIS
Mission	Military: Reconnaissance
Perigee/Apogee	176/369 km
Inclination	67.1°
Period	89.6 min
Launch vehicle	Soyuz
Launch site	Plesetsk
End of life

Decay	25 mar 1993


 Cosmos 2232

General

Designation	22321 / 93006A
Launch date	26 Jan 1993
Country of origin	CIS
Mission	Military: Early Warning
Perigee/Apogee	786/39557 km
Inclination	62.9°
Period	717.6 min
Launch vehicle	Molniya
Launch site	Plesetsk

Built by NPO PM, operated by the Russian Air Defense Forces (Voyska PVO)


 Cosmos 2233

General

Designation	22487 / 93008A
Launch date	9 Feb 1993 at 02:50 UT
Country of origin	CIS
Mission	Military: Navigation (Parus)
Perigee/Apogee	949/1007 km
Inclination	82.9°
Period	104.7 min
Launch vehicle	Cosmos
Launch site	Plesetsk
Technical data

Downlink frequency: 150.030 & 400.075 MHz

Plane 5


 Cosmos 2234

Also called Glonass 59

General

Designation	22512 / 93010A
Launch date	17 Feb 1993 at 20:30 UT
Country of origin	CIS
Mission	Navigation (Uragan)
Perigee/Apogee	19106/19152 km
Inclination	64.9°
Period	675.7 min
Launch vehicle	Proton #213
End of life

Out of service	yes


 Cosmos 2235

Also called Glonass 60 or Glonass 757

General

Designation	22513 / 93010B
Launch date	17 Feb 1993 at 20:30 UT
Country of origin	CIS
Mission	Navigation (Uragan)
Perigee/Apogee	19111/19147 km
Inclination	65°
Period	675.7 min
Launch vehicle	Proton #213
Technical data

Frequency (MHz)	L1 = 1602 + 0.5625 * channel L2 = 1246 + 0.4375 * channel
Channel	5
Plane	1
Slot	2


 Cosmos 2236

Also called Glonass 61 or Glonass 759

General

Designation	22514 / 93010C
Launch date	17 Feb 1993 at 20:30 UT
Country of origin	CIS
Mission	Navigation (Uragan)
Perigee/Apogee	19093/19165 km
Inclination	65°
Period	675.7 min
Launch vehicle	Proton #213
Technical data

Frequency (MHz)	L1 = 1602 + 0.5625 * channel L2 = 1246 + 0.4375 * channel
Channel	21
Plane	1
Slot	7


 Cosmos 2237

General

Designation	22565 / 93016A
Launch date	26 Mar 1993 at 02:25 UT
Country of origin	CIS
Mission	Military: SIGINT
Perigee/Apogee	846/852 km
Inclination	71.0°
Period	101.9 min
Launch vehicle	Zenit
Launch site	Tyuratan


 Cosmos 2238

General

Designation	22585 / 93018A
Launch date	30 Mar 1993 at 12:00 UT
Country of origin	CIS
Mission	Military: ocean reconnaissance (Eorsat)
Perigee/Apogee	127/143 km
Inclination	65.0°
Period	87.2 min
Launch vehicle	Cyclone 2
Launch site	Tyuratan
End of life

Decay	9 Dec 1994


 Cosmos 2239

General

Designation	22590 / 93020A
Launch date	1 Apr 1993 at 19:00 UT
Country of origin	CIS
Mission	Military: Navigation (Parus)
Perigee/Apogee	963/996 km
Inclination	82.9°
Period	104.7 min
Launch vehicle	Cosmos
Launch site	Plesetsk
Technical data

Downlink frequency: 149.970 & 399.92 MHz

Plane 4


 Cosmos 2240

General

Designation	22592 / 93021A
Launch date	2 Apr 1993 at 14:10 UT
Country of origin	CIS
Mission	Military: Reconnaissance (Yantar; 4th generation)
Perigee/Apogee	196/342 km
Inclination	62.8°
Period	89.6 min
Launch vehicle	Soyuz
Launch site	Plesetsk
End of life

Decay	7 Jun 1993
4th generation Russian reconnaissance satellites (extracted from JSR)

It appears that, unlike all earlier Soviet imaging reconnaissance satellites, they do not use the 1959-vintage Vostok satellite bus, although they are probably still made by the same company, the TsSKB (Central Specialized Design Bureau), formerly a subdivision of NPO Energiya. They were introduced in 1975, and originally had a lifetime of 30 days which was a big improvement on the Vostok satellites, at that time limited to 15 day missions. Later minor improvements increased the lifetime, first to 44 days and then, in 1984, to 59 days. The two flights so far this year [1993] show a further improvement, lasting 65 and 66 days. This modest increase is nevertheless significant as the first sign of an upgrade to this satellite class in a decade. By my count [Jonathan McDowell speaking], Kosmos-2240 is the 107th in the series, although the classification of several flights is controversial.


 Cosmos 2241

General

Designation	22594 / 93022A
Launch date	6 Apr 1993 at 19:10 UT
Country of origin	CIS
Mission	Military: Early Warning
Perigee/Apogee	832/39520 km
Inclination	63.6°
Period	717.7 min
Launch vehicle	Molniya
Launch site	Plesetsk


 Cosmos 2242

General

Designation	22626 / 93024A
Launch date	16 Apr 1993 at 08:00 UT
Country of origin	CIS
Mission	Military: SIGINT (Tselina)
Perigee/Apogee	632/666 km
Inclination	82.5°
Period	97 min
Launch vehicle	Cyclone
Launch site	Plesetsk
End of life

Cause	Exploded with the 3rd stage of the launcher
Decay	6 May 1993


 Cosmos 2243

General

Designation	22641 / 93028A
Launch date	27 Apr 1993 at 12:30 UT
Country of origin	CIS
Mission	Military: Reconnaissance (Kometa; 4th generation)
Perigee/Apogee	180/220 km
Inclination	70.4°
Period	88 min
Launch vehicle	Soyuz
Launch site	Tyuratam
End of life

Cause	Exploded with the 3rd stage of the launcher
Decay	6 May 1993


 Cosmos 2244

General

Designation	22643 / 93029A
Launch date	28 Apr 1993 at 03:35 UT
Country of origin	CIS
Mission	Military: ocean reconnaissance (Eorsat)
Perigee/Apogee	401/417 km
Inclination	65°
Period	92.8 min
Launch vehicle	Cyclone 2
Launch site	Tyuratan


 Cosmos 2245

General

Designation	22646 / 93030A
Launch date	11 May 1993
Country of origin	CIS
Mission	Military: telecommunications (Gonets)
Perigee/Apogee	1393/1415 km
Inclination	82.6°
Period	113.9 min
Launch vehicle	Cyclone
Launch site	Plesetsk


 Cosmos 2246

General

Designation	22647 / 93030B
Launch date	11 May 1993
Country of origin	CIS
Mission	Military: telecommunications (Gonets)
Perigee/Apogee	1397/1415 km
Inclination	82.6°
Period	113.9 min
Launch vehicle	Cyclone
Launch site	Plesetsk


 Cosmos 2247

General

Designation	22648 / 93030C
Launch date	11 May 1993
Country of origin	CIS
Mission	Military: telecommunications (Gonets)
Perigee/Apogee	1400/1415 km
Inclination	82.6°
Period	114.0 min
Launch vehicle	Cyclone
Launch site	Plesetsk


 Cosmos 2248

General

Designation	22649 / 93030D
Launch date	11 May 1993
Country of origin	CIS
Mission	Military: telecommunications (Gonets)
Perigee/Apogee	1398/1415 km
Inclination	82.6°
Period	113.9 min
Launch vehicle	Cyclone
Launch site	Plesetsk


 Cosmos 2249

General

Designation	22650 / 93030E
Launch date	11 May 1993
Country of origin	CIS
Mission	Military: telecommunications (Gonets)
Perigee/Apogee	1400/1415 km
Inclination	82.6°
Period	114.0 min
Launch vehicle	Cyclone
Launch site	Plesetsk


 Cosmos 2250

General

Designation	22651 / 93030F
Launch date	11 May 1993
Country of origin	CIS
Mission	Military: telecommunications (Gonets)
Perigee/Apogee	1400/1415 km
Inclination	82.6°
Period	114.0 min
Launch vehicle	Cyclone
Launch site	Plesetsk


 Cosmos 2251

General

Designation	22675 / 93036A
Launch date	16 Jun 1993 at 04:17 UT
Country of origin	CIS
Mission	Military: telecommunications
Perigee/Apogee	778/803 km
Inclination	74.0°
Period	100.7 min
Launch vehicle	Cosmos R14 (11K65M)
Launch site	Plesetsk

Is the 47th in a series of small low orbit communications satellites thought to be used by Russian military and intelligence services.


 Cosmos 2252

General

Designation	22687 / 93038A
Launch date	24 Jun 1994 at 04:12 UT
Country of origin	CIS
Mission	Military: telecommunications (Gonets)
Perigee/Apogee	1400/1415 km
Inclination	82.6°
Period	114.0 min
Launch vehicle	Cyclone
Launch site	Plesetsk


 Cosmos 2253

General

Designation	22688 / 93038B
Launch date	24 Jun 1994 at 04:12 UT
Country of origin	CIS
Mission	Military: telecommunications (Gonets)
Perigee/Apogee	1405/1424 km
Inclination	82.6°
Period	114.1 min
Launch vehicle	Cyclone
Launch site	Plesetsk


 Cosmos 2254

General

Designation	22689 / 93038C
Launch date	24 Jun 1994 at 04:12 UT
Country of origin	CIS
Mission	Military: telecommunications (Gonets)
Perigee/Apogee	1390/1412 km
Inclination	82.6°
Period	113.8 min
Launch vehicle	Cyclone
Launch site	Plesetsk


 Cosmos 2255

General

Designation	22690 / 93038D
Launch date	24 Jun 1994 at 04:12 UT
Country of origin	CIS
Mission	Military: telecommunications (Gonets)
Perigee/Apogee	1401/1413 km
Inclination	82.6°
Period	113.9 min
Launch vehicle	Cyclone
Launch site	Plesetsk


 Cosmos 2256

General

Designation	22691 / 93038E
Launch date	24 Jun 1994 at 04:12 UT
Country of origin	CIS
Mission	Military: telecommunications (Gonets)
Perigee/Apogee	1397/1412 km
Inclination	82.6°
Period	113.9 min
Launch vehicle	Cyclone
Launch site	Plesetsk


 Cosmos 2257

General

Designation	22692 / 93038F
Launch date	24 Jun 1994 at 04:12 UT
Country of origin	CIS
Mission	Military: telecommunications (Gonets)
Perigee/Apogee	1404/1419 km
Inclination	82.6°
Period	114.0 min
Launch vehicle	Cyclone
Launch site	Plesetsk


 Cosmos 2258

General

Designation	93044A / 22709
Launch date	8 Jul 1993 at 07:15 UT
Country of origin	CIS
Mission	Military: ocean reconnaissance (Eorsat)
Perigee/Apogee	400/417 km
Inclination	65°
Period	92.8 min
Launch vehicle	Cyclone 2
Launch site	Tyuratam
End of life

Decay	8 Jun 1995


 Cosmos 2259

General

Designation	22716 / 93045A
Launch date	14 Jul 1993 at 16:40 UT
Country of origin	CIS
Mission	Military: Reconnaissance (Yantar; 4th generation)
Perigee/Apogee	168/349 km
Inclination	67.1°
Period	89.7 min
Launch vehicle	Soyuz
Launch site	Plesetsk

It reentered after only 11 days in space. It was expected to stay up for two months.

End of life

Landed	25 Jul 1993


 Cosmos 2260

General

Designation	22721 / 93047A
Launch date	22 Jul 1993 at 08:56 UT
Country of origin	CIS
Mission	Military: Remote Sensing (Resurs T)
Perigee/Apogee	177/224 km
Inclination	82.3°
Period	88.5 min
Launch vehicle	Soyuz
Launch site	Plesetsk
End of life

Landed	5 Aug 1993


 Cosmos 2261

General

Designation	22741 / 93051A
Launch date	10 Aug 1993 at 15:00 UT
Country of origin	CIS
Mission	Military: Early Warning (Oko)
Perigee/Apogee	690/39674 km
Inclination	63°
Period	718 min
Launch vehicle	Molniya
Launch site	Plesetsk

built by NPO Lavochkin


 Cosmos 2262

General

Designation	22789 / 93057A
Launch date	7 Sep 1993 at 13:30 UT
Country of origin	CIS
Mission	Military: Reconnaissance (6th generation)
Perigee/Apogee	207/323 km
Inclination	65°
Period	89 min
Launch vehicle	Soyuz
Launch site	Tyuratam

Fifth in a new series of imaging satellites which fly two-month long missions. Previous satellites were 2031, 2101, 2163, and 2225.


 Cosmos 2263

General

Designation	22802 / 93059A
Launch date	16 Sep 1993 at 07:36 UT
Country of origin	CIS
Mission	Military: SIGINT
Perigee/Apogee	848/854 km
Inclination	71°
Period	102 min
Launch vehicle	Zenit
Launch site	Tyuratam LC45

The program had three consecutive launch failures in 1990-1992, but the last 4 launches have been successful.


 Cosmos 2264

General

Designation	22808 / 93060A
Launch date	2 Nov 1994 at 01:04 UT
Country of origin	CIS
Mission	Military: ocean reconnaissance (Eorsat)
Perigee/Apogee	402/418 km
Inclination	65°
Period	92.8 min
Launch vehicle	Cyclone 2
Launch site	Tyuratam LC90

It carries a low thrust engine to maintain precise separation with other EORSATs and uses radio interferometry to locate transmissions from ships.

End of life

Decay	7 Aug 1995


 Cosmos 2265

General

Designation	22875 / 93067A
Launch date	26 Oct 1993 at 10:00 UT
Country of origin	CIS
Mission	Military: calibration
Perigee/Apogee	291/1573 km
Inclination	83°
Period	103.5 min
Launch vehicle	Cosmos
Launch site	Plesetsk LC132


 Cosmos 2266

General

Designation	22888 / 93070A
Launch date	2 Nov 1993 at 12:10 UT
Country of origin	CIS
Mission	Military: Navigation (Parus)
Perigee/Apogee	945/1017 km
Inclination	83°
Period	104 min
Launch vehicle	Cosmos
Launch site	Plesetsk LC132
End of life

Out of service	yes
Technical data

Downlink frequency: 149.97 & 399.92 MHz

Plane 1


 Cosmos 2267

General

Designation	22904 / 93071A
Launch date	5 Nov 1993 at 08:25 UT
Country of origin	CIS
Mission	Military: Reconnaissance (advanced Yantar'; 5th generation)
Perigee/Apogee	241/282 km
Inclination	70.4°
Period	89 min
Launch vehicle	Soyuz
Launch site	Tyuratam LC1


 Cosmos 2268

General

Designation	22999 / 94011A
Launch date	12 Feb 1994 at 08:54 UT
Country of origin	CIS
Mission	Military: telecommunications (Gonets)
Perigee/Apogee	1411/1426 km
Inclination	82.57°
Period	114.2 min
Launch vehicle	Cyclone 3
Launch site	Plesetsk LC32


 Cosmos 2269

General

Designation	23000 / 94011B
Launch date	12 Feb 1994 at 08:54 UT
Country of origin	CIS
Mission	Military: telecommunications (Gonets)
Perigee/Apogee	1410/1421 km
Inclination	82.56°
Period	114.2 min
Launch vehicle	Cyclone 3
Launch site	Plesetsk LC32


 Cosmos 2270

General

Designation	23001 / 94011C
Launch date	12 Feb 1994 at 08:54 UT
Country of origin	CIS
Mission	Military: telecommunications (Gonets)
Perigee/Apogee	1406/1417 km
Inclination	82.57°
Period	114.05 min
Launch vehicle	Cyclone 3
Launch site	Plesetsk LC32


 Cosmos 2271

General

Designation	23002 / 94011D
Launch date	12 Feb 1994 at 08:54 UT
Country of origin	CIS
Mission	Military: telecommunications (Gonets)
Perigee/Apogee	1403/1415 km
Inclination	82.57°
Period	114 min
Launch vehicle	Cyclone 3
Launch site	Plesetsk LC32


 Cosmos 2272

General

Designation	23003 / 94011E
Launch date	12 Feb 1994 at 08:54 UT
Country of origin	CIS
Mission	Military: telecommunications (Gonets)
Perigee/Apogee	1396/1415 km
Inclination	82.57°
Period	113.9 min
Launch vehicle	Cyclone 3
Launch site	Plesetsk LC32


 Cosmos 2273

General

Designation	23004 / 94011F
Launch date	12 Feb 1994 at 08:54 UT
Country of origin	CIS
Mission	Military: telecommunications (Gonets)
Perigee/Apogee	1408/1416 km
Inclination	82.57°
Period	113.9 min
Launch vehicle	Cyclone 3 (11K68)
Launch site	Plesetsk LC32


 Cosmos 2274

General

Designation	23033 / 94018A
Launch date	17 Mar 1994 at 16:30 UT
Country of origin	CIS
Mission	Military: reconnaissance (Yantar'; 4th generation)
Perigee/Apogee	176.1/371.7 km
Inclination	67.15°
Period	89.65 min
Launch vehicle	Soyuz U
Launch site	Plesetsk LC43
End of life

Cause	Landed in Kazakhstan
Decay	21 May 1994


 Cosmos 2275

Also called Glonass 62 or Glonass 760

General

Designation	23043 / 94021A
Launch date	11 Apr 1994 at 08:49 UT
Country of origin	CIS
Mission	Navigation (Uragan)
Perigee/Apogee	19120/19197 km
Inclination	64°
Period	676 min
Launch vehicle	Proton #222
Technical data

Frequency (MHz)	L1 = 1602 + 0.5625 * channel L2 = 1246 + 0.4375 * channel
Channel	24
Plane	3
Slot	17


 Cosmos 2276

Also called Glonass 63 or Glonass 761

General

Designation	23044 / 94021B
Launch date	11 Apr 1994 at 08:49 UT
Country of origin	CIS
Mission	Navigation (Uragan)
Perigee/Apogee	19120/19197 km
Inclination	64°
Period	676 min
Launch vehicle	Proton #222
Technical data

Frequency (MHz)	L1 = 1602 + 0.5625 * channel L2 = 1246 + 0.4375 * channel
Channel	3
Plane	3
Slot	23


 Cosmos 2277

Also called Glonass 64 or Glonass 758

General

Designation	23045 / 94021C
Launch date	11 Apr 1994 at 08:49 UT
Country of origin	CIS
Mission	Navigation (Uragan)
Perigee/Apogee	19120/19197 km
Inclination	64°
Period	676 min
Launch vehicle	Proton #222
End of life

Out of service	28 Jul 1995
Technical data

Frequency (MHz)	L1 = 1602 + 0.5625 * channel L2 = 1246 + 0.4375 * channel
Channel	10
Plane	3
Slot	18


 Cosmos 2278

General

Designation	23087 / 94023A
Launch date	23 Apr 1994 at 08:02 UT
Country of origin	CIS
Mission	Military: SIGINT
Perigee/Apogee	854/858 km
Inclination	71°
Period	102 min
Launch vehicle	Zenit
Launch site	Tyuratam LC45


 Cosmos 2279

General

Designation	23092 / 94024A
Launch date	26 Apr 1994 at 02:14 UT
Country of origin	CIS
Mission	Military: Navigation (Parus)
Perigee/Apogee	955/1007 km
Inclination	83°
Period	104.7 min
Launch vehicle	Cosmos 3M
Launch site	Plesetsk LC133
Technical data

Donwlink frequencies: 149.940 & 399.840 MHz

Plane 6


 Cosmos 2280

General

Designation	23095 / 94025A
Launch date	28 Apr 1994
Country of origin	CIS
Mission	Military: reconnaissance (advanced Yantar'; 5th generation)
Perigee/Apogee	244/305 km
Inclination	70.3°
Period	90 min
Launch vehicle	Soyuz U
Launch site	Tyuratam LC31
End of life

Decay	22 Mar 1995


 Cosmos 2281

General

Designation	23119 / 94032A
Launch date	7 Jun 1994 at 07:20 UT
Country of origin	CIS
Mission	Military: reconnaissance (Vostok/Zenit or Oblik; 4th generation)
Perigee/Apogee	192/265 km
Inclination	82.6°
Period	88.7 min
Launch vehicle	Soyuz U
Launch site	Plesetsk

The number 2281 had earlier been assigned to an identical spacecraft that was launched on May 26 but failed to attain orbit.

This flight could be similar to Cosmos 2207 in 1992. The first Vostok based spy satellites were the Zenit 2 series. The first one to reach orbit, in 1962, was given the code name Cosmos 0004. The Zenit derived spy satellites have now been almost entirely phased out in favour of a newer bus called Yantar'.

End of life

Decay	29 Jun 1994


 Cosmos 2282

General

Designation	23168 / 94038A
Launch date	6 Jul 1994 at 23:59 UT
Country of origin	CIS
Mission	Military: early warning (Prognoz 2nd generation)
Geostationary orbit	24°W, inclined
Launch vehicle	Proton #224
Mass at launch	2600 kg
Technical data

Built by NPO Lavochkin

Equipped with a 500 kg 1 m diameter telescope


 Cosmos 2283

General

Designation	23182 / 94042A
Launch date	20 Jul 1994
Country of origin	CIS
Mission	Military: reconnaissance (Yantar'; 4th generation)
Perigee/Apogee	179/356 km
Inclination	67.1°
Period	89.5 min
Launch vehicle	Soyuz
Launch site	Plesetsk
End of life

Decay	29 Sep 1994


 Cosmos 2284

General

Designation	23187 / 94044A
Launch date	29 Jul 1994 at 09:29 UT
Country of origin	CIS
Mission	Military: reconnaissance (Kometa; 4th generation)
Perigee/Apogee	206/296 km
Inclination	70.4°
Period	89.2 min
Launch vehicle	Soyuz U
Launch site	Tyuratam LC31

It is presumably the 17th in the 'Kometa' series of topographic mapping satellites, based on the Yantar' spy satellite design. Kometa satellite imagery would be commercially distributed by AO Sovinformsputnik.

The last Kometa satellite, Kosmos-2243, was damaged during launch in Apr 1993. Typical mission length is 44 days. The first Kometa satellite was Kosmos-1246, in 1981. All the Kometa satellites are launched by Soyuz-U from Baykonur.

End of life

Decay	11 Sep 1994


 Cosmos 2285

General

Designation	23189 / 94045A
Launch date	2 Aug 1994 at 20:00 UT
Country of origin	CIS
Mission	Military: calibration or geodesy?
Perigee/Apogee	974/1013 km
Inclination	74°
Period	105 min
Launch vehicle	Cosmos 3M
Launch site	Plesetsk LC132


 Cosmos 2286

General

Designation	23194 / 94048A
Launch date	5 Aug 1994 at 01:12 UT
Country of origin	CIS
Mission	Military: early warning (Oko, means "eye")
Perigee/Apogee	747/39608 km
Inclination	63.4°
Period	718 min
Launch vehicle	Molniya
Launch site	Plesetsk

It carries a large telescope to detect ballistic missile launches.


 Cosmos 2287

Also called Glonass 65 or Glonass 767

General

Designation	23203 / 94050A
Launch date	11 Aug 1994 at 15:27 UT
Country of origin	CIS
Mission	Navigation (Uragan)
Perigee/Apogee	19109/19150 km
Inclination	64°
Period	676 min
Launch vehicle	Proton #225
Technical data

Frequency (MHz)	L1 = 1602 + 0.5625 * channel L2 = 1246 + 0.4375 * channel
Channel	22
Plane	2
Slot	12


 Cosmos 2288

Also called Glonass 66 or Glonass 770

General

Designation	23204 / 94050B
Launch date	11 Aug 1994
Country of origin	CIS
Mission	Navigation (Uragan)
Perigee/Apogee	19091/19168 km
Inclination	64°
Period	676 min
Launch vehicle	Proton #225
Technical data

Frequency (MHz)	L1 = 1602 + 0.5625 * channel L2 = 1246 + 0.4375 * channel
Channel	9
Plane	2
Slot	14


 Cosmos 2289

Also called Glonass 67 or Glonass 775

General

Designation	23205 94050C
Launch date	11 Aug 1994
Country of origin	CIS
Mission	Navigation (Uragan)
Perigee/Apogee	19126/19133 km
Inclination	64°
Period	676 min
Launch vehicle	Proton #225
Technical data

Frequency (MHz)	L1 = 1602 + 0.5625 * channel L2 = 1246 + 0.4375 * channel
Channel	22
Plane	2
Slot	16


 Cosmos 2290

General

Designation	23218 / 94053A
Launch date	26 Aug 1994 at 12:00 UT
Country of origin	CIS
Mission	Military: reconnaissance (Kuban; 7th generation)
Perigee/Apogee	211/292 km
Inclination	64.8°
Period	90.2 min
Launch vehicle	Zenith
Launch site	Tyuratam

This is a 7th generation "Kuban" reconnaissance satellite. Five such satellites had been launched in 1986 and 1987. Built by the TsSKB in Samara, they were prototypes of a new spacecraft generation. Civilian applications are knowned as Nika-T (microgravity), Nika-B (medical/biology) and Nika-E (high energy particles). Are supposed to weigh 9 tons and stay in orbit 90 to 120 days. The payload which takes place in a 4.3 m3 capsule weighs 1.2 t.

This specific satellite could be a digital imaging satellite. A commercial version should be available in September 1996; it should be equipped with a 2 m resolution imager.

In late March 1995 (between Mar 24 and 29) the spacecraft raised its apogee by 200 km, from an orbit of 181 x 382 km x 64.8° to 181 x 571 km x 64.8°, and four new small objects were tracked in the post-maneuver orbit. It seems likely that this marks the end of the Kosmos-2290 mission. Russian spy satellites are usually deorbited at the end of their mission, and it is not clear whether the orbit raise of Kosmos-2290 reflects a new operational regime, a new disposal strategy, a deorbit burn that went in the wrong direction, or (less likely) a tracking by US Space Command of a residual part of the spacecraft following recovery of a reentry vehicle.

End of life

Decay	4 Apr 1995


 Cosmos 2291

General

Designation	23267 / 94060A
Launch date	21 Sep 1994 at 17:53 UT
Country of origin	CIS
Mission	Military: telecommunications: Geizer
Geostationary orbit	80°E, inclined
Launch vehicle	Proton #226
Location

Begin	End	Position
L: 21 Sep 1994	late-Sep 1995	80°W
Nov 1995		14°W
Technical data

Specifications


 Cosmos 2292

General

Designation	23278 / 94061A
Launch date	27 Sep 1994 at 14:00 UT
Country of origin	CIS
Mission	Military: calibration (vektor?)
Perigee/Apogee	400/1951 km
Inclination	82.9°
Period	108.9 min
Launch vehicle	Cosmos 3M (11K65M)
Launch site	Plesetsk LC132


 Cosmos 2293

General

Designation	23336 / 94072A
Launch date	2 Nov 1994 at 01:04  UT
Country of origin	CIS
Mission	Military: ocean reconnaissance (Eorsat)
Perigee/Apogee	402/418 km
Inclination	65°
Period	92.8 min
Launch vehicle	Cyclone 2
Launch site	Tyuratam

Replaced Cosmos 2238


 Cosmos 2294

Also called Glonass 68 or Glonass 763

General

Designation	23396 / 94076A
Launch date	20 Nov 1994 at 00:09 UT
Country of origin	CIS
Mission	Navigation (Uragan)
Perigee/Apogee	19052/19207 km
Inclination	64.9°
Period	675 min
Launch vehicle	Proton #229
Technical data

Frequency (MHz)	L1 = 1602 + 0.5625 * channel L2 = 1246 + 0.4375 * channel
Channel	21
Plane	1
Slot	3


 Cosmos 2295

Also called Glonass 69 or Glonass 764

General

Designation	23397 / 94076B
Launch date	20 Nov 1994 at 00:09 UT
Country of origin	CIS
Mission	Navigation (Uragan)
Perigee/Apogee	19052/19207 km
Inclination	64.9°
Period	675 min
Launch vehicle	Proton #229
Technical data

Frequency (MHz)	L1 = 1602 + 0.5625 * channel L2 = 1246 + 0.4375 * channel
Channel	13
Plane	1
Slot	6


 Cosmos 2296

Also called Glonass 70 or Glonass 762

General

Designation	23398 / 94076C
Launch date	20 Nov 1994 at 00:09 UT
Country of origin	CIS
Mission	Navigation (Uragan)
Perigee/Apogee	19118/19114 km
Inclination	65°
Period	675 min
Launch vehicle	Proton #229
Technical data

Frequency (MHz)	L1 = 1602 + 0.5625 * channel L2 = 1246 + 0.4375 * channel
Channel	12
Plane	1
Slot	4


 Cosmos 2297

General

Designation	23404 / 94077A
Launch date	24 Nov 1994 at 09:16 UT
Country of origin	CIS
Mission	Military: intelligence
Perigee/Apogee	845/857 km
Inclination	71°
Period	102 min
Launch vehicle	Zenit 2
Launch site	Tyuratam LC45

The satellite carries an array of electronic intelligence detectors to monitor radio emissions.


 Cosmos 2298

General

Designation	23431 / 94083A
Launch date	20 Dec 1994 at 05:11 UT
Country of origin	CIS
Mission	Military: telecommunications
Perigee/Apogee	785/810 km
Inclination	74°
Period	100.8 min
Launch vehicle	Cosmos 3M
Launch site	Plesetsk LC132

Satellites are launched into this orbit at the rate of about one a year; Cosmos 2298 is the 48th to reach orbit since Kosmos-372 in 1970. Western analysts have suggested that the series are communications satellites for sensitive military or intelligence communications.


 Cosmos 2299

General

Designation	23441 / 94086A
Launch date	26 Dec 1994 at 22:27 UT
Country of origin	CIS
Mission	Military: telecommunications (Gonets)
Perigee/Apogee	1402/1415 km
Inclination	82.6°
Period	114 min
Launch vehicle	Cyclone 3
Launch site	Plesetsk LC32


 Cosmos 2300

General

Designation	23442 / 94086B
Launch date	26 Dec 1994 at 22:27 UT
Country of origin	CIS
Mission	Military: telecommunications (Gonets)
Perigee/Apogee	1410/1414 km
Inclination	82.5°
Period	114 min
Launch vehicle	Cyclone 3
Launch site	Plesetsk LC32


 Cosmos 2301

General

Designation	23443 / 94086C
Launch date	26 Dec 1994 at 22:27 UT
Country of origin	CIS
Mission	Military: telecommunications (Gonets)
Perigee/Apogee	1410/1414 km
Inclination	82.5°
Period	114 min
Launch vehicle	Cyclone 3
Launch site	Plesetsk LC32


 Cosmos 2302

General

Designation	23444 / 94086D
Launch date	26 Dec 1994 at 22:27 UT
Country of origin	CIS
Mission	Military: telecommunications (Gonets)
Perigee/Apogee	1413/1423 km
Inclination	82.6°
Period	114.2 min
Launch vehicle	Cyclone 3
Launch site	Plesetsk LC32


 Cosmos 2303

General

Designation	23445 / 94086E
Launch date	26 Dec 1994 at 22:27 UT
Country of origin	CIS
Mission	Military: telecommunications (Gonets)
Perigee/Apogee	1413/1430 km
Inclination	82.6°
Period	114.3 min
Launch vehicle	Cyclone 3
Launch site	Plesetsk LC32


 Cosmos 2304

General

Designation	23446 / 94086F
Launch date	26 Dec 1994 at 22:27 UT
Country of origin	CIS
Mission	Military: telecommunications (Gonets)
Perigee/Apogee	1412/1417 km
Inclination	82.6°
Period	114.1 min
Launch vehicle	Cyclone 3
Launch site	Plesetsk LC32


 Cosmos 2305

General

Designation	23453 / 94088A
Launch date	29 Dec 1994 at 11:31 UT
Country of origin	CIS
Mission	Military: reconnaissance (advanced Yantar'; 5th generation)
Perigee/Apogee	231/288 km
Inclination	64.9°
Period	89.7 min
Launch vehicle	Soyuz U
Launch site	Tyuratam LC31

This spacecraft raises its orbit periodically

End of life

Cause	deorbit
Decay	18 Dec 1995


 Cosmos 2306

General

Designation	23501 / 95008A
Launch date	2 Mar 1995 at 13:00 UT
Country of origin	CIS
Mission	Military: calibration (cosmos 816 type)
Perigee/Apogee	469/516 km
Inclination	65.8°
Period	94.5 min
Launch vehicle	Cosmos 3M
Launch site	Plesetsk

Releases a series of small objects at intervals, to act as calibration targets for the radars.


 Cosmos 2307

Also called Glonass 71 or Glonass 765

General

Designation	23511 / 95009A
Launch date	7 Mar 1995 at 09:23 UT
Country of origin	CIS
Mission	Navigation (Uragan)
Perigee/Apogee	19132 km
Inclination	64°
Period	279 min
Launch vehicle	Proton #232
Technical data

Frequency (MHz)	L1 = 1602 + 0.5625 * channel L2 = 1246 + 0.4375 * channel
Channel	1
Plane	3
Slot	20


 Cosmos 2308

Also called Glonass 72 or Glonass 766

General

Designation	23512 / 95009B
Launch date	7 Mar 1995 at 09:23 UT
Country of origin	CIS
Mission	Navigation (Uragan)
Perigee/Apogee	19132 km
Inclination	64°
Period	279 min
Launch vehicle	Proton #232
Technical data

Frequency (MHz)	L1 = 1602 + 0.5625 * channel L2 = 1246 + 0.4375 * channel
Channel	10
Plane	3
Slot	22


 Cosmos 2309

Also called Glonass 73 or Glonass 777

General

Designation	23513 / 95009C
Launch date	7 Mar 1995 at 09:23 UT
Country of origin	CIS
Mission	Navigation (Uragan)
Perigee/Apogee	19132 km
Inclination	64°
Period	279 min
Launch vehicle	Proton #232
Technical data

Frequency (MHz)	L1 = 1602 + 0.5625 * channel L2 = 1246 + 0.4375 * channel
Channel	3
Plane	3
Slot	19


 Cosmos 2310

General

Designation	23526 / 95012A
Launch date	22 Mar 1995 at 04:05 UT
Country of origin	CIS
Mission	Military: Navigation (Parus)
Perigee/Apogee	980/1010 km
Inclination	82.9°
Period	105 min
Launch vehicle	Cosmos 3M
Launch site	Plesetsk
Technical data

Downlink frequencies: 149.910 & 399.760 MHz

Plane 2


 Cosmos 2311

General

Designation	23530 / 95014A
Launch date	22 Mar 1995 at 16:45 UT
Country of origin	CIS
Mission	Military: reconnaissance (Yantar')
Perigee/Apogee	169/334 km
Inclination	67.1°
Period	89.54 min
Launch vehicle	Soyuz U
Launch site	Plesetsk

Design lifetime: 2 months

End of life

Decay	31 May 1995


 Cosmos 2312

General

Designation	23584 / 95026A
Launch date	24 May 1995 at 20:10 UT
Country of origin	CIS
Mission	Military: early warning (Oko)
Perigee/Apogee	614/40166 km
Inclination	62.8°
Period	709 min
Launch vehicle	Molniya M
Launch site	Plesetsk

Other birds of this program are: 2063, 2097, 2176, 2217, 2222, 2232, 2241, 2261, 2286

Technical data

Specifications

Prime contractor	NPO Lavotchkin
Platform
Mass at launch	2300 kg
Mass in orbit
Length
Width
Height
Stabilization
DC power	2800 W
Design lifetime	5 years?

Equipped with an infrared telescope


 Cosmos 2313

General

Designation	23596 / 95028A
Launch date	8 Jun 1995 at 04:30 UT
Country of origin	CIS
Mission	Military: ocean reconnaissance (Eorsat)
Perigee/Apogee	403/415 km
Inclination	65°
Period	92.7 min
Launch vehicle	Cyclone 2
Launch site	Tyuratam

Replaced Cosmos 2258


 Cosmos 2314

General

Designation	23601 / 95031A
Launch date	28 Jun 1995 at 18:30 UT
Country of origin	CIS
Mission	Military: reconnaissance (Yantar')
Perigee/Apogee	166/339 km
Inclination	67.1°
Period	89.6 min
Launch vehicle	Soyuz U
Launch site	Plesetsk

Built by TsSKB (Central Specialized Design Bureau) of Samara, Russia and will obtain images for the Russian GRU intelligence agency. Has the ability to raise its orbit.

End of life

Decay	6 Sep 1995


 Cosmos 2315

General

Designation	23603 / 95032A
Launch date	5 Jul 1995 at 03:10 UT
Country of origin	CIS
Mission	Navigation (Kurs)
Perigee/Apogee	988/1027 km
Inclination	82.9°
Period	105 min
Launch vehicle	Cosmos 3M
Launch site	Plesetsk LC132 pad 1

Part of a new series: the Kurs system enables maritime traffic control and messages to individual vessels.

Technical data

Downlink frequencies: 150 & 400 MHz

Plane 11


 Cosmos 2316

Also called Glonass 74 or Glonass 780

General

Designation	23620 / 95037A
Launch date	24 Jul 1995 at 15:52 UT
Country of origin	CIS
Mission	Navigation (Uragan)
Perigee/Apogee	19101/19134 km
Inclination	64.8°
Period	675 min
Launch vehicle	Proton #234
Technical data

Frequency (MHz)	L1 = 1602 + 0.5625 * channel L2 = 1246 + 0.4375 * channel
Channel	4
Plane	2
Slot	15


 Cosmos 2317

Also called Glonass 75 or Glonass 781

General

Designation	23621 / 95037B
Launch date	24 Jul 1995 at 15:52 UT
Country of origin	CIS
Mission	Navigation (Uragan)
Perigee/Apogee	19101/19134 km
Inclination	64.8°
Period	675 min
Launch vehicle	Proton #234
Technical data

Frequency (MHz)	L1 = 1602 + 0.5625 * channel L2 = 1246 + 0.4375 * channel
Channel	9
Plane	2
Slot	10


 Cosmos 2318

Also called Glonass 76 or Glonass 785

General

Designation	23622 / 95037C
Launch date	24 Jul 1995 at 15:52 UT
Country of origin	CIS
Mission	Navigation (Uragan)
Perigee/Apogee	19101/19134 km
Inclination	64.8°
Period	675 min
Launch vehicle	Proton #234
Technical data

Frequency (MHz)	L1 = 1602 + 0.5625 * channel L2 = 1246 + 0.4375 * channel
Channel	4
Plane	2
Slot	11


 Cosmos 2319

General

Designation	23653 / 95045A
Launch date	30 Aug 1995 at 19:33 UT
Country of origin	CIS
Mission	Military: Telecommunications: Geizer
Geostationary orbit	80°E
Launch vehicle	Proton #235
Technical data

Specifications


 Cosmos 2320

General

Designation	23674 / 95051A
Launch date	29 Sep 1995 at 04:25 UT
Country of origin	CIS
Mission	Military: reconnaissance (advanced Yantar'; 5th generation)
Perigee/Apogee	189/304 km
Inclination	64.9°
Period	89 min
Launch vehicle	Soyuz U
Launch site	Tyuratam LC31


 Cosmos 2321

General

Designation	23676 / 95052A
Launch date	6 Oct 1995 at 03:23 UT
Country of origin	CIS
Mission	Military: Navigation (Parus)
Perigee/Apogee	257/790 km
Inclination	82.9°
Period	95.1 min
Launch vehicle	Cosmos 3M
Launch site	Plesetsk LC132

The second stage of the launcher malfunctioned; thus the satellite couldn't reach the intended 960 km x 1010 km x 83° orbit.

End of life

Out of service	6 Oct 1995


 Cosmos 2322

General

Designation	23704 / 95058A
Launch date	31 Oct 1995 at 20:19 UT
Country of origin	CIS
Mission	Military: SIGINT (Tselina 2)
Perigee/Apogee	849/852 km
Inclination	71°
Period	101.9 min
Launch vehicle	Zenit 2 (11K77)
Launch site	Tuyratam LC45L

The booster is said to reduce air pollution to a minimum... The Zenit rocket produced by Ukraine is fuelled by a mixture of liquid oxygen and kerosene. Zenit was fired 14 times since 1987 with 3 failures.


 Cosmos 2323

Also called Glonass 776

General

Designation	23734 / 95068A
Launch date	14 Dec 1995 at 06:10 UT
Country of origin	CIS
Mission	Navigation (Uragan)
Perigee/Apogee	19114/19141 km
Inclination	64.8°
Period	675 min
Launch vehicle	Proton #238
Technical data

Frequency (MHz)	L1 = 1602 + 0.5625 * channel L2 = 1246 + 0.4375 * channel
Channel
Plane	2
Slot


 Cosmos 2324

Also called Glonass 778

General

Designation	23735 / 95068B
Launch date	14 Dec 1995 at 06:10 UT
Country of origin	CIS
Mission	Navigation (Uragan)
Perigee/Apogee	19117/19139 km
Inclination	64.8°
Period	675 min
Launch vehicle	Proton #238
Technical data

Frequency (MHz)	L1 = 1602 + 0.5625 * channel L2 = 1246 + 0.4375 * channel
Channel
Plane	2
Slot


 Cosmos 2325

Also called Glonass 782

General

Designation	23736 / 95068C
Launch date	14 Dec 1995 at 06:10 UT
Country of origin	CIS
Mission	Navigation (Uragan)
Perigee/Apogee	19109/19148 km
Inclination	64.8°
Period	675 min
Launch vehicle	Proton #238
Technical data

Frequency (MHz)	L1 = 1602 + 0.5625 * channel L2 = 1246 + 0.4375 * channel
Channel
Plane	2
Slot


 Cosmos 2326

General

Designation	23748 / 95071A
Launch date	20 Dec 1995 at 00:52 UT
Country of origin	CIS
Mission	Military: ocean reconnaissance (Eorsat)
Perigee/Apogee
Inclination
Period
Launch vehicle	Cyclone 2
Launch site	Tyuratam LC90


 Cosmos 2327

General

Designation	23773 / 96004A
Launch date	16 Jan 1996 at 15:34 UT
Country of origin	CIS
Mission	Military: Navigation (Parus)
Perigee/Apogee	947/1020 km
Inclination	83°
Period	105 min
Launch vehicle	Cosmos 3M
Launch site	Plesetsk
Technical data

Downlink frequencies: 149.970 & 399.920 MHz

Plane 1


 Cosmos 2328

General

Designation	23790 / 96009D?
Launch date	19 Feb 1996 at 00:58 UT
Country of origin	CIS
Mission	Military: telecommunications (Gonets)
Perigee/Apogee	~1400 km
Inclination	~82°
Period
Launch vehicle	Cyclone 3
Launch site	Plesetsk


 Cosmos 2329

General

Designation	23791 / 96009E?
Launch date	19 Feb 1996 at 00:58 UT
Country of origin	CIS
Mission	Military: telecommunications (Gonets)
Perigee/Apogee	~1400 km
Inclination	~82°
Period
Launch vehicle	Cyclone 3
Launch site	Plesetsk


 Cosmos 2330

General

Designation	23792 / 96009F?
Launch date	19 Feb 1996 at 00:58 UT
Country of origin	CIS
Mission	Military: telecommunications (Gonets)
Perigee/Apogee	~1400 km
Inclination	~82°
Period
Launch vehicle	Cyclone 3
Launch site	Plesetsk


 Cosmos 2331

General

Designation	23818 / 96016A
Launch date	14 Mar 1996 at 17:45 UT
Country of origin	CIS
Mission	Military: reconnaissance (Yantar')
Perigee/Apogee	164/355 km
Inclination	67.1°
Period
Launch vehicle	Soyuz U
Launch site	Plesetsk

This Russian Defense Ministry payload carries a US DoD secondary experiment launched as part of the Space Test Program, the BINRAD package which will attempt to detect the presence of beryllium at orbital altitudes. BINRAD was flown twice before on Russian civilian Resurs-F remote sensing missions.


 Launch vehicles

Section directed by Jean-Jacques Serra

A:	Ariane	ASLV	Atlas
B:	Black Arrow
C:	Conestoga
D:	Delta	Diamant
H:	H2
I:	ISAS vehicles	ISRO vehicles
L:	LLV
M:	Mu
P:	Pegasus	Proton	PSLV
R:	Rokot
S:	Scout	SLV 3	Start	STS
T:	Taurus	Thor	Titan 4
World Launch Vehicle Overview

Vehicle	First launch	LEO capacity (kg)	GTO capacity (kg)	Comments
CIS (Sheldon / DoD)				Detailed soviet chart here
Zemiorka (A / SL1)	4 Oct 1957	1300		2-stage (--> 1958)
Luna (A1 / SL2)	(Aug 1958) 2 Jan 1959			3-stage (--> 1960)
Vostok (A1 / SL3)	15 May 1960	4700		3-stage
Molniya (A2e / SL6)	(10 Oct 1960) 4 Feb 1961		1600 (THEO)	4-stage, Molniya or Prognoz orbit
Cosmos (B1 / SL7)	16 Mar 1962	450		2-stage (--> 1977), 144 launches
Voskhod (A2 / SL4)	16 Nov 1963	5500		3-stage
Cosmos (C1 / SL8)	18 Aug 1964	1400		2-stage
Proton (D / SL9)	16 Jul 1965	12500		2-stage (--> 1968)
Cosmos (F1r / SL11)	17 Sep 1966			2-stage (--> 1971)
Soyuz (A2 / SL4)	28 Nov 1966	7500		3-stage
Proton (D1e / SL12)	10 Mar 1967		4600 (GEO)	4-stage
Cosmos (F1m / SL11)	27 Oct 1967	4000		2-stage
N1 (G / SL15?)	(21 Feb 1969)			Lunar vehicle launcher
Proton (D1 / SL13)	16 Nov 1968	20000		3-stage
Cyclone 3 (F2 / SL14)	24 Jun 1977	5500		3-stage
Zenit (J1 / SL16)	21 Jun 1985	15000		2-stage
Energia (K1 / SL17)	15 May 1987	140000	18000 (GEO)	shuttle, 2 successful flights
Start	25 Mar 1993	500		5-stage
Rokot	26 Dec 1994	1850		3-stage (RS18K)
United States
Vanguard	(6 Dec1957) 17 Mar 1958	25		3-stage (--> 1959), 3 successful flights
Juno 1	31 Jan 1958	40		4-stage (--> 1959)
Thor Able	(17 Aug 1958) 11 Oct 1958	200		3-stage (--> Thor Delta)
Juno 2	6 Dec 1958	50		4-stage (--> 1961)
Atlas	18 Dec 1958	1300		Mercury launcher
Thor Agena	28 Feb 1959	1000		2-stage (--> LTT Agena)
Atlas Able	(26 Nov 1959)			3-stage (--> 1960)
Atlas Agena	(26 Feb 1960) 24 May 1960	2300		2-stage (--> 1978)
Thor Ablestar	13 Apr 1960			2-stage (--> 1965)
Thor Delta	(13 May 1960) 18 Aug 1960			3-stage, (--> Delta)
Scout	(4 Dec 1960) 16 Feb 1961			4-stage (--> 1994)
Atlas Centaur	(8 May 1962) 16 Feb 1961	5600	2250	4-stage (--> Atlas 2)
Saturn 1	29 Jan 1964	6800		2/3-stage (--> 1965)
Titan 2	08 Apr 1964	3500		Gemini launcher
Titan 3A	(01 Sep 1964) 10 Dec 1964			3-stage (--> 1965)
Titan 3C	18 Jun 1965	11300	4500	3-stage + boosters (--> Titan 34D)
Saturn 1B	05 Jul 1966	12900		Apollo launcher
Titan 3B	29 Jul 1966	3500	700 (THEO)	3-stage (--> Titan 34B)
LTTAT Agena	09 Aug 1966	2000		2-stage (--> 1972)
Saturn 5	09 Nov 1967	140000		Lunar vehicle launcher
Titan 3D	15 Jun 1971	13000		3-stage + boosters (--> Titan 34D)
Delta 29xx	09 Nov 1972	2000	720	2/3-stage (--> Delta 39xx)
Delta 39xx	13 Dec 1975		1250	2/3 stage (--> Delta 2)
STS	12 Apr 1981	24200	5900 (with IUS)	Space Shuttle
Titan 34D	30 Oct 1982	15800	1900	2/3-stage + boosters (--> Titan 4)
Delta-2 69xx	14 Feb 1989	4000	1400	Interim Delta 2
Titan 4	14 Jun 1989	17700	5500	2/3-stage + boosters
Pegasus	5 Apr 1990	400		air launched rocket
Delta-2 79xx	26 Nov 1990	5000	1610
Atlas 2	7 Dec 1991	6400	2700	2-stage
Atlas 2A	10 Jun 1992	6800	2900	2-stage
Atlas 2AS	16 Dec 1993	8400	3600	2-stage + boosters
Taurus	13 Mar 1994	1400		4-stage
Pegasus XL	(27 Jun 1994)	455		air launched rocket
LLV 1	(15 Aug 1995)	1000		3-stage
Conestoga	(23 Oct 1995)	2100		4-stage
Delta 3	1998?	9200	4200
Atlas RD 180	?
Titan 2S	?
Titan 4SRMU	?
Pegasus Turbo	?
France
Diamant A	26 Nov 1965	80		3-stage (--> 1967)
Diamant B	10 Mar 1970	115		3-stage (--> 1973)
Diamant BP4	6 Feb 1975	150		3-stage (--> 1975)
Japan
Lambda-4S	(26 Sep 1966) 11 Feb 1970	20		4-stage, 1 successful flight
Mu-4S	(25 Sep 1970) 16 Feb 1971	75		3-stage (--> 1972)
Mu-3C	16 Feb 1974	85		3-stage (--> 1976)
N1	9 Sep 1975			3-stage (--> 1982)
Mu-3H	19 Feb 1977	100		3-stage (--> 1979)
Mu-3S1	17 Feb 1981	200		3-stage (--> 1984)
N2	11 Feb 1981		350	3-stage (--> 1987)
Mu-3S2	8 Jan 1985	400
H1	13 Aug 1986	3200	1100	3-stage (--> 1995)
H2	3 Feb 1994	10500	4000 (2000 to GEO)	2-stage + boosters
J1	exp. 1996	870		solid 3-stage consist of H2 strap-on first stage + 2 stages of Mu-3S2
Mu 5	exp. 1997	2000		solid 3-stage
China
Long March 1D	no launches	1000		liquid/solid 3-stage
Long March 1	(01 Nov 1969) 24 Apr 1970			3-stage (--> 1971)
Long March 2A	(05 Nov 1974)			No successful flight
FB 1	26 Jul 1975			2-stage (LEO) (--> 1981)
Long March 2C	26 Nov 1975	2500	1000 + PKM	liquid 2-stage 14 success
Long March 3	29 Jan 1984	5000	1400	liquid 3-stage 5 success; 2 failed to reach correct orbit
Long March 4	6 Sep 1988	4000		liquid 3-stage 2 success
Long March 2E	16 Jul 1990	9200	3370 with PKM 3370 with LM3A 3rd stage	liquid 2-stage + 4 liquid strap-ons 3 success, 2 failures
Long March 2D	9 Aug 1992	3300		liquid 2-stage 2 success
Long March 3A	8 Feb 1994	7200	2500	liquid 2-stage 2 success
Long March 3B	(14 Feb 1996) exp. 1996		4800	liquid 3-stage + 4 liquid strap-ons consist of Long March 3A with 4 2E strap-ons
Long March 3C	exp. 1997		3700	liquid 3-stage + 2 liquid strap-ons consist of Long March 3A with 2 2E strap-ons
United Kingdom
Black Arrow	(1 Sep 1970) 28 Oct 1971			3-stage One successful flight
Europe
Europa 1 F8	(30 Nov 1968)			No successful flight
Europa 2	(05 Nov 1971)			No successful flight
Ariane 1	24 Dec 1979		1700	3-stage (--> 1986)
Ariane 3	4 Aug 1984		2580	3-stage + boosters
Ariane 2	30 May 1986		2065	3-stage
Ariane 4, 44LP	15 Jun 1988	8300	4030
Ariane 4, 44L	4 Jun 1989	9600	4460
Ariane 4, 40	22 Jan 1990	4900	2020	3-stage
Ariane 4, 42P	20 Nov 1990	6100	2740
Ariane 4, 44P	4 Apr 1991	6900	3290
Ariane 4, 42L	12 May 1993	7400	3350
Ariane 5	exp. Apr 1996	18000	6800	liquid 2-stage + 2 solid strap-ons
India
SLV 3	(10 Aug 1979) 18 Jul 1980	40		4-stage (--> 1983)
ASLV	(24 Mar 1987) 20 May 1992	150		solid 4-stage + 2 solid strap-ons (--> 1994)
PSLV	(20 Sep 1993) 15 Oct 1994	3000		solid/liquid 4-stage + 2 solid strap-ons
GSLV	late 1997	8000	2500
Israel
Shavit	19 Sep 1988	150		solid 3-stage


 Soviet launch vehicles

Gunter Krebs

Sheldon / Dod	Name	Article	Designation	Comment
A / SL1		R7	8K71
A / SL1	Sputnik	?	8K71PS	for the first 2 Sputniks
A / SL2	Sputnik	?	8A91	for Sputnik (3) failure and Sputnik-3
A1 / SL3	Vostok L (Luna?)	?	8Kxx	for early Lunas and the first Korabl-Sputnik
A1 / SL3	Vostok K	?	8KxxK	for Korabl-Sputniks and Vostoks
A1 / SL3	Vostok	?	8A92	for Cosmos series (Zenit) spysats and early Meteors
A1 / SL3	Vostok M	?	8A92M	for sunsynchronous missions
A2 / SL4	Voskhod	?	11A57 ?	for the first missons and for Voskhod
A2 / SL4	Soyuz	?	11A511	for Soyuz capsules
A2 / SL4	Soyuz M	?	11A511M
A2 / SL4	Soyuz L	?	11A511L	to lift Cosmos 398 class Lunar lander tests into LEO
A2 / SL4	Soyuz U	?	11A511U	the current model for unmanned missions
A2 / SL4	Soyuz U2	?	11A511U2	the current version for manned missions (and possibly for Kuban type spysats)
A2e / SL6	Molniya	?	8K78	was used only until 1966
A2e / SL6	Molniya M	?	8K78M	the current model
Ae / SL5	Sputnik-Polyot	?	11A??	Polyot launch vehicle
A1m / SL10	?	?	11A510	Cosmos 125 / 102 launch vehicle
B1 / SL7	?	?	63S1	difference unknown
B1 / SL7	Cosmos 2	?	11K63	difference unknown
C1 / SL8	?	?	65S1	Tyuratam launch
C1 / SL8	Cosmos 3	?	11K65	Tyuratam launch
C1 / SL8	Cosmos 3M	?	11K65M	Kapustin Yar and Plesetsk launch
D / SL9	Proton	UR500	?	two stage test version
D1 / SL13	Proton K	UR500K		three stage version for LEO
D1e / SL12	Proton K Block D	UR-500K Block D	?	for early interplanetary probes
D1e / SL12	Proton K Block DM	UR-500K Block DM	?	for early GEO missions
D1e / SL12	Proton K Block DM2	UR-500K Block DM2	?	uprated version of Block DM
D1e / SL12	Proton K Block DM2M	UR-500K Block DM2M	?	lightwight version of Block DM2 for higher payloads
G1e / SL15		N1 / L3	?
G1e / SL15		N1 / L3 (7L)	L	N-1 L3 (7L) had different boattail
F1r / SL11		R36-0	8K69	for FOBS
F1m / SL11	Cyclone M (or 2)	?	11K69
F2 / SL12	Cyclone 3	?	11K68	for Eorsat and Rorsat
J1 / SL16	Zenit 2	?	11K77
K1 / SL17	Energiya	?	?


needs sorting! (preparing new launcher items)

Cyclone 2

two stage rocket based on the R-36 (SS-9) ballistic missile. Built by NPO Youjnoe (OKB 586). Was used to launch the FOBS (orbital bombs), the ASAT (anti-satellites) and the Eorsat and Rorsat

Cyclone-2 first flew in the late 1960s

Cyclone 3

Cyclone 3: built in Ukraine. in 1977 the S5M third stage was added to Cyclone 2 to make the Cyclone 3, which is now the standard light launch vehicle used by the Russians.

Cosmos 3M

Cosmos 3M, built by PO Polyot of Omsk, is derived from the R-14 (NATO designation SS-5) IRBM built originally by the Yangel design bureau.

H2

H2 rockets have problems... and next launch (the 4th) is not before mid-1996. The government decided (9 Aug 95) to modify it so that I can orbit as heavy as 3 to 4 tons satellites (currently=2). The test model should be available in 2001.

Delta 3

McDonnell Douglas announced plans for private development of Delta III, based on an anchor-customer contract for 10+ launches (including the first, in early 1998) from Hughes. D3 will be capable of about 4.2 tons to GTO (roughly twice the current Delta payload). LEO payload about 9.2 tons.

D3 is an odd configuration. The strap-on solids get a bit longer and fatter, and three (out of nine) acquire vectoring nozzles. The first stage mostly stays the same diameter, but shortly above the solid strap-ons, it bulges out to 13.1ft dia. The first-stage fuel tank is above the bulge.  More important, the 13.1ft dia continues upward, with a completely new LH2/LOX second stage and a new wide payload fairing. The engine for the second stage has not yet been chosen, but it will be an existing Western engine. D3 design will emphasize proven technology and maximum use of existing Delta hardware.

Much attention on the new second stage. Some have claimed it's an H-2 second stage -- especially since McDD has a long history of work with Mitsubishi on the major Japanese launchers -- but McDD says no:  "frankly, it's too expensive" (although use of some Japanese hardware is possible). Others claim it's going to be a single-engine Centaur, but McDD doesn't like Centaur's balloon tanks or its common bulkhead, and says D3 will have neither (although it will probably use Centaur's insulation scheme).

Proton

Should be replaced by the Angara booster The first stage will use the same kerosene-LOX four-engine cluster as Zenit; the second stage will use a single Energia-derived LH2-LOX engine. The configuration is rather odd: a cylindrical center body reminiscent of a Zenit (holding the fuel), with a pair of large drop tanks slung on the outside of each stage to hold the LOX. The initial configuration will launch 26t into a 63deg orbit from Plesetsk (slightly more than Proton from Baikonur); a third stage (LH2-LOX) will be added to put 4.5t payloads into GSO.

There is talk of an Angara offshoot using a modified second stage air-launched from an An-124, launching 6t into 51deg at about $1500/kg.

Burlak

Russian project of LEO launcher released from a bomber. Burlak will be a wingless two-stage liquid-fuel vehicle, derived from (unspecified) missile technology.  Payload to LEO would be up to 800kg at perhaps $5000/kg.


 Ariane

European launch vehicle program

Type	First launch	Last launch	LEO/GTO capacity (kg)	Number of launches
1	24 Dec 1979	22 Feb 1986	/1700	11 (2 failures)
2	30 May 1986	2 Apr 1989	/2065	6 (1 failure)
3	4 Aug 1984	12 Jul 1989	/2580	11 (1 failure)
4, 40	22 Jan 1990	07 Jul 1995	4900/2020	5
4, 42P	20 Nov 1990	10 Jun 1995	6100/2740	7 (1 failure)
4, 44P	4 Apr 1991	5 Feb 1996	6900/3290	7
4, 42L	12 May 1993	19 Oct 1995	7400/3350	4
4, 44LP	15 Jun 1988	14 Mar 1996	8300/4030	17 (1 failure)
4, 44L	4 Jun 1989	12 Jan 1996	9600/4460	16 (1 failure)

With flight 73 the H10-3 third stage configuration was introduced; it enables a maximum of 4700 kg to be delivered on GTO with Ariane 4, 44L


Ariane

[launch vehicle index]

Ariane L01 Ariane L02 Ariane L03 Ariane L04 Ariane L05 Ariane L06 Ariane L07 Ariane L08 Ariane V09 Ariane V10 Ariane V11 Ariane V12 Ariane V13 Ariane V14 Ariane V15 Ariane V16 Ariane V17 Ariane V18 Ariane V19 Ariane V20	Ariane V21 Ariane V22 Ariane V23 Ariane V24 Ariane V25 Ariane V26 Ariane V27 Ariane V28 Ariane V29 Ariane V30 Ariane V31 Ariane V32 Ariane V33 Ariane V34 Ariane V35 Ariane V36 Ariane V37 Ariane V38 Ariane V39 Ariane V40	Ariane V41 Ariane V42 Ariane V43 Ariane V44 Ariane V45 Ariane V46 Ariane V47 Ariane V48 Ariane V49 Ariane V50 Ariane V51 Ariane V52 Ariane V53 Ariane V54 Ariane V55 Ariane V56 Ariane V57 Ariane V58 Ariane V59 Ariane V60	Ariane V61 Ariane V62 Ariane V63 Ariane V64 Ariane V65 Ariane V66 Ariane V67 Ariane V68 Ariane V69 Ariane V70 Ariane V71 Ariane V72 Ariane V73 Ariane V74 Ariane V75 Ariane V76 Ariane V77 Ariane V78 Ariane V79 Ariane V80	Ariane V81 Ariane V82 Ariane V83 Ariane V84


foo title

SYLDA: SYstème de Lancement Double d'Ariane

SPELDA: Système Porteur Externe pour le Lancement Double Ariane

Ariane 5

Premier essai du booster à Kourou le 16 Feb 1993. Fabriqué en guyane, ce booster est une fusée à poudre de 30 m de longueur. Sa pousée est à elle seule comparable à la plus puissante des versions d'Ariane 4.

Deux boosters de ce type flanqueront un corps central muni, d'un gros moteur à hydrogène Vulcain.

Le premier lancement d'une Ariane 5 est prévu au cours du second semestre 1995. Ariane 5 présentera la caractéristique d'être plus fiable qu'Ariane 4, tout en étant moins chère de 10 %. Son aptitude à effectuer des lancements doubles de gros satellites devrait être un atout supplémentaire pour l'Europe.


 Ariane L01

General

Launch id	79104
Launch date	24 Dec 1979
Launch site	Kourou
Type	1
Payload mass
Payload	A: Cat 1
GTO	203/35996 km


 Ariane L02

General

Launch date	23 May 1980 at 09:29:39 UT
Launch site	Kourou
Type	1
Payload mass
Payload	Cat 2 Firewheel Oscar 09 (failure)
Failure cause	First stage motor injection failure


 Ariane L03

General

Launch id	81057
Launch date	19 Jun 1981 at 12:32:52 UT
Launch site	Kourou
Type	1
Payload mass	1635 kg
Payload	A: Meteosat 2 B: Apple C: Cat 3
GTO	201/36206 km


 Ariane L04

General

Launch id	81122
Launch date	20 Dec 1981 at 01:29 UT
Launch site	Kourou
Type	1
Payload mass	> 1056 kg
Payload	A: Marecs A B: Cat 4

First night launch


 Ariane L05

General

Launch date	10 Sep 1982 at 01:12 UT
Launch site	Kourou
Type	1
Payload mass	1476 kg
Payload	Marecs B1 Sirio 2
Failure cause	3rd stage motor turbo pump failure


 Ariane L06

General

Launch id	83058
Launch date	16 Jun 1983 at 11:59 UT
Launch site	Kourou
Type	1
Payload mass	1205 kg
Payload	A: Eutelsat 1F1 B: Oscar 10

First successful launch with the Sylda system


 Ariane L07

General

Launch id	83105
Launch date	18 Oct 1983 at 23:54 UT
Launch site	Kourou
Type	1
Payload mass	1870 kg
Payload	A: Intelsat 507


 Ariane L08

General

Launch id	84023
Launch date	5 Mar 1984 at 00:50 UT
Launch site	Kourou
Type	1
Payload mass	1900 kg
Payload	A: Intelsat 508


 Ariane V09

General

Launch id	84049
Launch date	22 May 1984
Launch site	Kourou
Type	1
Payload mass	1195 kg
Payload	A: Spacenet 1

First launch operated by Arianespace


 Ariane V10

General

Launch id	84081
Launch date	4 Aug 1984 at 11:32:54 UT
Launch site	Kourou
Type	3
Payload mass	2395 kg
Payload	A: Eutelsat 1F2 B: Telecom 1A

First Ariane 3 launch


 Ariane V11

General

Launch id	84114
Launch date	10 Nov 1984 at 01:14 UT
Launch site	Kourou
Type	3
Payload mass	2251 kg
Payload	A: Spacenet 2 B: Marecs B2
GTO	200/36.022 km, inclination: 7.01°


 Ariane V12

General

Launch id	85015
Launch date	8 Feb 1985
Launch site	Kourou
Type	3
Payload mass	2310 kg
Payload	A: Arabsat 1A B: Brazilsat A1


 Ariane V13

General

Launch id	85035
Launch date	8 May 1985 at 00:15 UT
Launch site	Kourou
Type	3
Payload mass	2480 kg
Payload	A: GStar 1 B: Telecom 1B


 Ariane V14

General

Launch id	85056
Launch date	2 Jul 1985
Launch site	Kourou
Type	1
Payload mass	960 kg
Payload	ESA's comet Halley interceptor Giotto

Recovery of the first stage failed because the parachutes didn't open


 Ariane V15

General

Launch date	13 Sep 1985
Launch site	Kourou
Type	3
Payload mass	2380 kg
Payload	Eutelsat 1F3 Spacenet 3
Failure cause	One of the 3rd stage motors didn't switch on. President Mitterrand was there. It was Friday 13th


 Ariane V16

General

Launch id	86019
Launch date	22 Feb 1986 at 01:44:35 UT
Launch site	Kourou
Type	1
Payload mass	2438 kg
Payload	A: Spot 1 B: Viking

First launch towards North to put the satellites on a polar orbit. Last launch of an Ariane 1


 Ariane V17

General

Launch id	86026
Launch date	28 Mar 1986
Launch site	Kourou
Type	3
Payload mass	2410 kg
Payload	A: GStar 2 B: Brazilsat A2

First launch on ELA 2


 Ariane V18

General

Launch date	30 May 1986 at 00:53 UT
Launch site	Kourou
Type	2
Payload mass	1900 kg
Payload	Intelsat 514
Failure cause	One the 3rd stage motors didn't switch on

First launch of an Ariane 2


 Ariane V19

General

Launch id	87078
Launch date	16 Sep 1987
Launch site	Kourou
Type	3
Payload mass	2435 kg
Payload	A: Optus A3 B: Eutelsat 1F4


 Ariane V20

General

Launch id	87095
Launch date	21 Nov 1987
Launch site	Kourou
Type	2
Payload mass	2144 kg
Payload	A: Tvsat 1


 Ariane V21

General

Launch id	88018
Launch date	11 Mar 1988 at 23:28 UT
Launch site	Kourou
Type	3
Payload mass	2405 kg
Payload	A: Spacenet 3R B: Telecom 1C
GTO	202/36087 km, inclination: 7.03°


 Ariane V22

General

Launch id	88040
Launch date	17 May 1988 at 00:58 UT
Launch site	Kourou
Type	2
Payload mass	1978 kg
Payload	A: Intelsat 513
GTO	463/35948 km


 Ariane V23

General

Launch id	88051
Launch date	15 Jun 1988
Launch site	Kourou
Type	4, 44LP
Payload mass
Payload	A: Meteosat 3 B: Oscar 13 C: Panamsat 1

First launch of Ariane 4


 Ariane V24

General

Launch id	88063
Launch date	21 Jul 1988 at 23:12 UT
Launch site	Kourou
Type	3
Payload mass	2337 kg
Payload	A: Insat 1C B: Eutelsat 1F5
GTO	198/35993 km, inclination: 7°


 Ariane V25

General

Launch id	88081
Launch date	8 Sep 1988 at 23:00 UT
Launch site	Kourou
Type	3
Payload mass	2511 kg
Payload	A: GStar 3 B: SBS 5


 Ariane V26

General

Launch id	88098
Launch date	28 Oct 1988 at 02:17 UT
Launch site	Kourou
Type	2
Payload mass	2100 kg
Payload	A: TDF 1
GTO	266/36096 km inclination: 3.94°


 Ariane V27

General

Launch id	88109
Launch date	11 Dec 1988 at 00:33 UT
Launch site	Kourou
Type	4, 44LP
Payload mass	3230 kg
Payload	A: Skynet 4B B: Astra 1A


 Ariane V28

General

Launch id	89006
Launch date	27 Jan 1989 at 01:21 UT
Launch site	Kourou
Type	2
Payload mass	1981 kg
Payload	A: Intelsat 515
GTO	463/35959 km, inclination: 8°


 Ariane V29

General

Launch id	89020
Launch date	6 Mar 1989 at 23:29 UT
Launch site	Kourou
Type	4, 44LP
Payload mass	2976 kg
Payload	A: Jcsat 1 B: Meteosat 4


 Ariane V30

General

Launch id	89027
Launch date	2 Apr 1989 at 02:28 UT
Launch site	Kourou
Type	2
Payload mass	2089 kg
Payload	A: TELE X

Last launch of an Ariane 2


 Ariane V31

General

Launch id	89041
Launch date	5 Jun 1989
Launch site	Kourou
Type	4, 44L
Payload mass	3907 kg
Payload	A: Superbird A1 B: DFS 1


 Ariane V32

General

Launch id	89053
Launch date	12 Jul 1989 at 00:14 UT
Launch site	Kourou
Type	3
Payload mass	2595 kg
Payload	A: Olympus

Last launch of an Ariane 3 and last use of ELA 1


 Ariane V33

General

Launch id	89062
Launch date	8 Aug 1989
Launch site	Kourou
Type	4, 44LP
Payload mass	3284 kg
Payload	A: Tvsat 2 B: Hipparcos


 Ariane V34

General

Launch id	89087
Launch date	27 Oct 1989 at 23:05 UT
Launch site	Kourou
Type	4, 44LP
Payload mass	4200 kg
Payload	A: Intelsat 602
GTO	199.6/35965 km


 Ariane V35

General

Launch id	90005
Launch date	22 Jan 1990 at 01:35 UT
Launch site	Kourou
Type	4, 40
Payload mass	1990 kg
Payload	A: Spot 2 B: Uosat 3 C: Uosat 4 D: Pacsat E: Dove F: Webersat G: Lusat

The ASAP 1 (Ariane Structure for Auxiliary Payload) structure which carries up to 200 kg was used


 Ariane V36

General

Launch date	22 Feb 1990
Launch site	Kourou
Type	4, 44L
Payload mass	3782 kg
Payload	Superbird D Yuri 2X
Failure cause	A rag was forgotten in a water pipe for D motor's cooling


 Ariane V37

General

Launch id	90063
Launch date	24 Jul 1990
Launch site	Kourou
Type	4, 44L
Payload mass	4114 kg
Payload	A: TDF 2 B: DFS 2
GTO	300/35933 km, inclination: 4°


 Ariane V38

General

Launch id	90079
Launch date	30 Aug 1990 at 22:46 UT
Launch site	Kourou
Type	4, 44LP
Payload mass	3280 kg
Payload	A: Skynet 4C B: Eutelsat 2F1


 Ariane V39

General

Launch id	90091
Launch date	12 Oct 1990
Launch site	Kourou
Type	4, 44L
Payload mass	4208 kg
Payload	A: SBS 6 B: Galaxy 6


 Ariane V40

General

Launch id	90100
Launch date	20 Nov 1990
Launch site	Kourou
Type	4, 42P
Payload mass	2464 kg
Payload	A: Satcom C1 B: GStar 4


 Ariane V41

General

Launch id	91003
Launch date	15 Jan 1991
Launch site	Kourou
Type	4, 44L
Payload mass	3720 kg
Payload	A: Italsat 1 B: Eutelsat 2F2


 Ariane V42

General

Launch id	91015
Launch date	2 Mar 1991
Launch site	Kourou
Type	4, 44LP
Payload mass	3261 kg
Payload	A: Astra 1B B: Meteosat 5


 Ariane V43

General

Launch id	91026
Launch date	5 Apr 1991
Launch site	Kourou
Type	4, 44P
Payload mass	2923 kg
Payload	A: Anik E2


 Ariane V44

General

Launch id	91050
Launch date	17 Jul 1991
Launch site	Kourou
Type	4, 40
Payload mass	2513 kg
Payload	A: ERS 1 B: Uosat 5 C: Orbcomm X D: Tubsat_A E: Sara

ASAP 2 carried the micro-satellites


 Ariane V45

General

Launch id	91055
Launch date	14 Aug 1991
Launch site	Kourou
Type	4, 44L
Payload mass	4296 kg
Payload	A: Intelsat 605


 Ariane V46

General

Launch id	91067
Launch date	27 Sep 1991
Launch site	Kourou
Type	4, 44P
Payload mass	2923 kg
Payload	A: Anik E1


 Ariane V47

General

Launch id	91075
Launch date	29 Oct 1991
Launch site	Kourou
Type	4, 44L
Payload mass	4330 kg
Payload	A: Intelsat 601


 Ariane V48

General

Launch id	91084
Launch date	16 Dec 1991
Launch site	Kourou
Type	4, 44L
Payload mass	3605 kg
Payload	A: Telecom 2A B: Inmarsat 2F3


 Ariane V49

General

Launch id	92010
Launch date	26 Feb 1992
Launch site	Kourou
Type	4, 44L
Payload mass	3870 kg
Payload	A: Superbird B1 B: Arabsat 1C


 Ariane V50

General

Launch id	92021
Launch date	15 Apr 1992
Launch site	Kourou
Type	4, 44L
Payload mass	3600 kg
Payload	A: Telecom 2B B: Inmarsat 2F4


 Ariane V51

General

Launch id	92041
Launch date	9 Jul 1992 at 22:42 UT
Launch site	Kourou
Type	4, 44L
Payload mass	3750 kg
Payload	A: Insat 2A B: Eutelsat 2F4


 Ariane V52

General

Launch id	92052
Launch date	10 Aug 1992
Launch site	Kourou
Type	4, 42P
Payload mass	2200 kg
Payload	A: Topex Poseidon B: Kitsat A C: S80T

ASAP 3 carried the micro-satellites


 Ariane V53

General

Launch id	92060
Launch date	10 Sep 1992
Launch site	Kourou
Type	4, 44LP
Payload mass	> 2120 kg
Payload	A: Hispasat 1A B: Satcom C3


 Ariane V54

General

Launch id	92072
Launch date	28 Oct 1992 at 00:15 UT
Launch site	Kourou
Type	4, 42P
Payload mass	2725 kg
Payload	A: Galaxy 7


 Ariane V55

General

Launch id	92084
Launch date	1 Dec 1992
Launch site	Kourou
Type	4, 42P
Payload mass	2780 kg
Payload	A: Superbird A2


 Ariane V56

General

Launch id	93031
Launch date	12 May 1993 at 00:56:32 UT
Launch site	Kourou
Type	4, 42L
Payload mass	2854 kg
Payload	A: Astra 1C B: Arsène


 Ariane V57

General

Launch id	93039
Launch date	25 Jun 1993 at 00:18 UT
Launch site	Kourou
Type	4, 42P
Payload mass	2988 kg
Payload	A: Galaxy 4


 Ariane V58

General

Launch id	93048
Launch date	22 Jul 1993 at 22:58:55 UT
Launch site	Kourou
Type	4, 44LP
Payload mass	4020 kg
Payload	A: Hispasat 1B B: Insat 2B
GTO	200/35957 km, inclination: 6.96°


 Ariane V59

General

Launch id	93061
Launch date	26 Sep 1993 at 01:45 UT
Launch site	Kourou
Type	4, 40
Payload mass	2117 kg
Payload	A: Spot 3 B: Stella C: Eyesat D: Itamsat E: Healthsat F: ASAP 4 (22828) G: Posat H: Kitsat B

ASAP 4 carried the micro-satellites


 Ariane V60

General

Launch id	93066
Launch date	22 Oct 1993 at 06:46 UT
Launch site	Kourou
Type	4, 44LP
Payload mass	3692 kg
Payload	A: Intelsat 701


 Ariane V61

General

Launch id	93073
Launch date	20 Nov 1993 at 01:17 UT
Launch site	Kourou
Type	4, 44LP
Payload mass	3500 kg
Payload	A: Solidaridad 1 B: Meteosat 6


 Ariane V62

General

Launch id	93078
Launch date	18 Dec 1993 at 01:27 UT
Launch site	Kourou
Type	4, 44L
Payload mass	3940 kg
Payload	A: DBS 1 B: Thaicom 1


 Ariane V63

General

Launch date	24 Jan 1994 at 21:37 UT
Launch site	Kourou
Type	4, 44LP
Payload mass	3663 kg
Payload	Eutelsat 2F5 Turksat 1A
Failure cause	3rd stage motor failure (H10+ turbopump)


 Ariane V64

General

Launch id	94034
Launch date	17 Jun 1994 at 07:07 UT
Launch site	Kourou
Type	4, 44LP
Payload mass	3800 kg
Payload	A: Intelsat 702 B: STRV 1A C: STRV 1B


 Ariane V65

General

Launch id	94040
Launch date	8 Jul 1994 at 23:05:32 UT
Launch site	Kourou
Type	4, 44L
Payload mass	4035 kg
Payload	A: Panamsat 2 B: Yuri 3N
GTO	199.6/35977 km; inclination: 7°

Total mass boosted into orbit: 4618 kg


 Ariane V66

General

Launch id	94049
Launch date	10 Aug 1994 at 23:05 UT
Launch site	Kourou
Type	4, 44LP
Payload mass
Payload	A: Brazilsat B1 B: Turksat 1B


 Ariane V67

General

Launch id	94058
Launch date	9 Sep 1994 at 00:29 UT
Launch site	Kourou
Type	4, 44P
Payload mass	3300 kg
Payload	A: Telstar 402


 Ariane V68

General

Launch id	94065
Launch date	8 Oct 1994 at 01:07 UT
Launch site	Kourou
Type	4, 44L
Payload mass
Payload	A: Solidaridad 2 B: Thaicom 2


 Ariane V69

General

Launch id	94070
Launch date	1 Nov 1994 at 00:37 UT
Launch site	Kourou
Type	4, 42P
Payload mass	2924 kg
Payload	A: Astra 1D


 Ariane V70

General

Launch date	1 Dec 1994 at 22:57 UT
Launch site	Kourou
Type	4, 42P
Payload mass	2985 kg
Payload	Panamsat 3
Failure cause	3rd stage gave only 70% of its power

Boosters had been enhanced to transport the satellite which was 200 kilos heavier than normal maximal weight. The third stage was a H-10-3 type, first time used; this didn't cause the failure.


 Ariane V71

General

Launch id	95016
Launch date	28 Mar 1995 at 23:14:20 UT
Launch site	Kourou
Type	4, 44LP
Payload mass
Payload	A: Brazilsat B2 B: Hotbird 1 +1 meteo satellite?

Third stage was a H-10+ type


 Ariane V72

General

Launch id	95021
Launch date	21 Apr 1995 at 01:44 UT
Launch site	Kourou
Type	4, 40
Payload mass	2400 kg
Payload	ERS 2

Last flight with a H-10+ type 3rd stage


 Ariane V73

General

Launch id	95023
Launch date	17 May 1995 at 6:34 UT
Launch site	Kourou
Type	4, 44LP
Payload mass	4180 kg
Payload	Intelsat 706

Third stage was a H-10-3 type (second use) It increases the performance by 60 to 140 kg depending on the launcher version


 Ariane V74

General

Launch id	95029
Launch date	10 Jun 1995 at 00:24 UT
Launch site	Kourou
Type	4, 42P
Payload mass	2934 kg
Payload	DBS 3


 Ariane V75

General

Launch id	95033
Launch date	7 Jul 1995 at 16:23 UT
Launch site	Kourou
Type	4, 40
Payload mass	2634 kg
Payload	A: Hélios 1A B: Cerise C: UPMSat 1


 Ariane V76

General

Launch id	95040
Launch date	3 Aug 1995 at 22:58 UT
Launch site	Kourou
Type	4, 42L
Payload mass	3043 kg
Payload	A: Panamsat 4
Injection orbit	485.2 km x 35934 km x 4.21 deg


 Ariane V77

General

Launch id	95044
Launch date	29 Aug 1995 at 06:41 UT
Launch site	Kourou
Type	4, 44P
Payload mass	3398 kg
Payload	A: N Star A
GTO	199 km x 35922 km x 6.96 deg


 Ariane V78

General

Launch id	95049
Launch date	24 Sep 1995 at 00:06 UT
Launch site	Kourou
Type	4, 42L
Payload mass	3410 kg
Payload	A: Telstar 402R
GTO	249.1 km x 35919 km x 7.03°


 Ariane V79

General

Launch id	95055
Launch date	19 Oct 1995 at 00:38 UT
Launch site	Kourou
Type	4, 42L
Payload mass	3010 kg
Payload	A: Astra 1E
GTO	485.5 km x 36077 km x 4.19°


 Ariane V80

General

Launch id	95062
Launch date	17 Nov 1995 at 01:20 UT
Launch site	Kourou
Type	4, 44P
Payload mass
Payload	A: ISO
GTO	500 km x 71860 km x 5.25°

Equipped with an H-10-III upper stage, but with the No. 02 type payload fairing.


 Ariane V81

General

Launch id	95067
Launch date	6 Dec 1995 at 23:23 UT
Launch site	Kourou
Type	4, 44L
Payload mass	4296 kg
Payload	A: Telecom 2C B: Insat 2C
GTO	199.8 x 35976 km x 7°

Total mass boosted into orbit: 4804 kg


 Ariane V82

General

Launch id	96002
Launch date	12 Jan 1996 at 23:10 UT
Launch site	Kourou
Type	4, 44L
Payload mass	4368 kg
Payload	A: Panamsat 3R B: Measat 1
GTO	199.6 x 35992 km x 6.99°


 Ariane V83

General

Launch id	96007
Launch date	5 Feb 1996 at 07:19 UT
Launch site	Kourou
Type	4, 44P
Payload mass	3420 kg
Payload	N Star B
GTO	199.7 x 35952 km x 7°


 Ariane V84

General

Launch id	96015
Launch date	14 mar 1996 at 07:11 UT
Launch site	Kourou
Type	4, 44LP
Payload mass	4175 kg
Payload	Intelsat 707
GTO	199.7 x 35913 km x 7.04°


 Atlas

Jean-Jacques Serra

Launchers operated by Martin Marietta Launch Services, formerly General Dynamics. Since mid-1995 the launchers are marketed by International Launch Services (ILS)

Origins of Atlas

Atlas without top stage

Atlas with an Agena stage

Atlas with solid top stage

Atlas with a Centaur stage

Origin: Inter Continental Ballistic Missile (ICBM) of first generation

In January 1955 the General Dynamics' Convair division was selected to build the Atlas system. In 1946 this firm was awarded a contract to design a 8000 km range ICBM: the MX-774. Three of those were launched in 1948 before the project was cancelled. Notheless those studies had lead to 3 major innovations: the engine with gimbaled nozzle, the monocoque structure and the releasable payload.

In the mid-50ies the problems related to high altitude ignition of liquid ergol engines were not solved. The only known solution was to ignite them all at takeoff: the Russians picked a cylinder structure for their Zemiorka while the Americans opted for a one-and-a-half stage vehicle. A main Rocketdyne LR89 rocket with 25 tons thrust was supported during about 140 seconds by 2 LR105 jettisonable motors of 68 tons thrust each. The propulsion bay containing 3 motors was named MA-1. Those engines consumed ergols (liquid oxygen and kerosene) provided by the same tanks. On each side a Vernier LR101 rocket of 0.45 ton provided fine tuning of the thrust. The missile itself was 3.05 m diameter and 22.9 m in height (with an Mk2 Reentry Vehicle) and weighed over 110 tons.

On 11 Jun 1957 for its first test, the missile was only propulsed by its lateral motors... but it failed. The first success occured at the third try, on 17 Dec 1957. On 2 Aug 1958 the first 3-motor Atlas (named version B) ranged over 4000 km and the nominal range was achieved on 28 Nov 1958 (version C). Less than a month later on 18 Dec 1958 Atlas was used for a space mission: Score.

The propulsion system kept on evolving, first as a missile then as a space launcher (see chart 1). The first improved MA-2 was used for the Atlas-D ICBM. Then the MA-3 was introduced as a simplified version for the Atlas-E and -F ICBMs and derived launchers. The MA-5 was a civilian version of the MA-2; it was used by Atlas SLV-3 until the MA-5A version became available for Atlas-2.

Atlas propulsion system [chart 1]

Designation	Year of first launch	Main engine Thrust (ton)	Main engine SI (sec.)	Additional engines Thrust (ton)	Additional engines SI (sec.)	Application
MA-1	1957	24.5	210	136	245	Atlas A, B, C
MA-2	1958	25.8	213	140	248	Atlas D
MA-3	1960	25.8	214	149.5	250	Atlas E, F, launchers
MA-5	1961	27.4	220	171	259	launchers
MA-5A	1991	27.4	220	191.8	264	launchers

Atlas was equipped with the top stages of Thor Able -derived from those of Vanguard- in 1959. This launcher named Atlas Able was to launch the Pioneer probes to the Moon. But after 3 failures between November 1959 and December 1960 it was abandonned.

Statistics

Between 1956 and 1989, 189 MA-1/MA-2, 238 MA-3 and 213 MA-5 propulsion systems were manufactured that is 640 Atlas. The great majority of those Altas were used as ICBM. Thus the 150th Atlas was fired on 7 Nov 1962 and within those 150 rockets only 31 did launch satellites.


Atlas

[launch vehicle index]

Origins of Atlas

Atlas without top stage

Atlas with an Agena stage

Atlas with solid top stage

Atlas with a Centaur stage


 Atlas without top stage

Jean-Jacques Serra

The Score experiment proved that Atlas could orbit payloads without any top stage. So it was decided to use it for the manned Mercury program, without major modifications. The Redstone rocket used for the first tests of this program wasn't powerful enough to orbit the 1300 kg Mercury spacecraft.

Atlas launches for the Mercury program [chart 2]

#	Launch id	Payload	Launch date	Type	Status (orbit in perigee x apogee x inc. x period)
1	n/a	Mercury MA-1	29 Jul 1960	D	Ballistic flight
2	n/a	Mercury MA-2	21 Feb 1961	D	Ballistic flight
3	n/a	Mercury MA-3	25 Apr 1961	D	Failled to orbit
4	61025	Mercury MA-4	13 Sep 1961	D	161 x 256 x 32.8 x 88.4
5	61033	Mercury MA-5 (chimpanzee Enos)	29 Nov 1961	D	150 x 242 x 32.6 x 88.3
6	62003	Mercury MA-6 (J. Glenn)	20 Feb 1962	D	161 x 263 x 32.5 x 88.6
7	62019	Mercury MA-7 (S. Carpenter)	24 May 1962	D	161 x 268 x 32.5 x 88.5
8	62052	Mercury MA-8 (W. Schirra)	03 Oct 1962	D	161 x 283 x 32.5 x 88.8
9	63015	Mercury MA-9 (G. Cooper)	15 May 1963	D	161 x 267 x 32.5 x 88.7

Notes: All launches from Cape Canaveral


 Atlas Agena

Jean-Jacques Serra

Agena was used from 1959 to 1987 and is the most used top stage with 350 launches mostly for military payloads. The first version Agena-A was equipped with a Bell 8096 (nitric acid/UDMH) engine capable of 6.8 tons thrust during 2 minutes. It couldn't be re-ignited unlike the Agena-B version introduced in 1960. Agena-D used a more powerful motor capable of 7.25 tons thrust for 4 minutes. Those stages were all 1.52 m in diameter but had a variable length.

Most of the payloads had military missions:

- reconnaissance (Samos, KH 6 and KH 7)

- early warning (Midas, Vela, BMEWS)

- SIGINT (Ryolithe)

But Atlas Agena also launched:

- lunar probes (Ranger, Lunar Orbiter) & planetary probes (Mariner)

- target for the Gemini manned program (GATV, ATDA)

- scientific (OAO, OGO, Seasat) and technology (Snapshot, ATS) satellites

Atlas Agena launches [chart 3]

#	Launch id	Payload	Launch date	Site	Type	Status (orbit in perigee x apogee x inclination x period)
1	n/a	Midas-01	26 Feb 1960	C	Agena-A	Failure
2	60006	Midas 02	24 May 1960	C	Agena-A
3	n/a	Samos 1	11 Oct 1960	V		Failure
4	61001	Samos 2	31 Jan 1961	V	Agena-B
5	61018	Midas 03	12 Jul 1961	V	Agena-B
6	61021	Ranger-1	23 Aug 1961	C	Agena-B	169 x 502 x 32.9 x 90.6
7	n/a	Samos 3	09 Sep 1961	V	Agena-B	Failure
8	61028	Midas 04	21 Oct 1961	V	Agena-B
9	61032	Ranger-2	18 Nov 1961	V	Agena-B	158 x 237 x 33.3 x 88.3
10	n/a	Samos 4	22 Nov 1961	V	Agena-B	Failure
11	61035	Samos 5	22 Dec 1961	V	Agena-B	244 x 702 x 89.6 x 91.1
12	62001	Ranger-3	26 Jan 1962	C	Agena-B	Solar orbit
13	62007	Samos 6?	07 Mar 1962	V	Agena-B	249 x 635 x 90.9 x 93.9
14	62010	Midas 05	09 Apr 1962	V	Agena-B
15	62012	Ranger-4	23 Apr 1962	C	Agena-B	Moon impact
16	62016	KH 7 prototype? (FTV 2401)	26 Apr 1962	V	Agena-B
17	62023	KH 7 prototype? (FTV 2402)	17 Jun 1962	V	Agena-B
18	62030	KH 7 prototype? (FTV 2403)	18 Jul 1962	V	Agena-B	184 x 236 x 96.1 x 88.7
19	n/a	Mariner-1	22 Jul 1962	C	Agena-B	Failure
20	62035	KH 7 prototype? (FTV 2404)	05 Aug 1962	V	Agena-B	205 x 205 x 96.3 x 88.6
21	62041	Mariner-2	27 Aug 1962	C	Agena-B	Probe to Venus
22	62055	Ranger-5	18 Oct 1962	C	Agena-B	Solar orbit
23	62064	KH 7 prototype? (FTV 2405)	11 Nov 1962	V	Agena-B	206 x 206 x 96 x 88.7
24	n/a	Midas	17 Dec 1962	V	Agena-B	Failure
25	63014	Midas 06	09 May 1963	V	Agena-B
26	n/a	Midas	12 Jun 1963	V	Agena-D	Failure
27	63028	KH 7-01	12 Jul 1963	V	Agena-D
28	63030	Midas 07	18 Jul 1963	V	Agena-B
29	63036	KH7#2	06 Sep 1963	V	Agena-D	168 x 263 x 94.4 x 89.1
30	63039	Vela Hotel-1/2 (+)	17 Oct 1963	C	Agena-D	107000 x 113000 x 38.3 x 6270
31	63041	KH7#3	25 Oct 1963	V	Agena-D	144 x 332 x 99.1 x 89
32	63051	KH7#4	18 Dec 1963	V	Agena-D	122 x 266 x 97.9 x 88.5
33	64007	Ranger-6	30 Jan 1964	C	Agena-B	Lunar impact
34	64009	KH7#5 (OPS 2423)	25 Feb 1964	V	Agena-D	173 x 190 x 95.7 x 88.2
35	64012	KH7#6 (OPS 3435)	11 Mar 1964	V	Agena-D	163 x 202 x 95.7 x 88.2
36	64020	KH7#7 (OPS 3743)	23 Apr 1964	V	Agena-D	150 x 336 x 103.6 x 89.4
37	64024	KH7#8 (OPS 3592)	19 May 1964	V	Agena-D	141 x 380 x 101.1 x 89.7
38	64036	KH7#9 (OPS 3684) OPS 4923	06 Jul 1964	V	Agena-D	121 x 346 x 92.9 x 89.2
39	64040	Vela 3 (OPS 3662) Vela 4 (OPS 3674) ERS 13	17 Jul 1964	C	Agena-D	98000 x 108000 x 39.6 x 6023
40	64041	Ranger-7	28 Jul 1964	C	Agena-B	Moon impact
41	64045	KH7#10 (OPS 3802 + 3316)	14 Aug 1964	V	Agena-D	149 x 307 x 95.5 x 89
42	64054	OGO 1	05 Sep 1964	C	Agena-B
43	64058	KH7#11 (OPS 4262)	23 Sep 1964	V	Agena-D	145 x 303 x 92.9 x 89
44	n/a	KH7	08 Oct 1964	V	Agena-D	Failure
45	64068	KH7#12 (OPS 4384 + 5063)	23 Oct 1964	V	Agena-D	139 x 271 x 95.6 x 88.6
46	64073	Mariner-3	05 Nov 1964	C	Agena-D	Probe to Mars
47	64077	Mariner-4	28 Nov 1964	C	Agena-D	Probe to Mars
48	64079	KH7#13 (OPS 4439)	04 Dec 1964	V	Agena-D	158 x 357 x 97 x 89.7
49	65005	KH7#14 (OPS 4703)	23 Jan 1965	V	Agena-D	146 x 291 x 102.5 x 88.9
50	65010	Ranger-8	17 Feb 1965	C	Agena-B	Moon impact
51	65019	KH7#15 (OPS 4920)	12 Mar 1965	V	Agena-D	155 x 247 x 107.7 x 88.5
52	65023	Ranger-9	21 Mar 1965	C	Agena-B	Moon impact
53	65027	SNAPSHOT (OPS 4682) Secor 4 (EGRS 4)	03 Apr 1965	V	Agena-D	1282 x 1313 x 90 x 111.6
54	65031	KH7#16 (OPS 4983 + 6717)	28 Apr 1965	V	Agena-D	180 x 259 x 95.6 x 89
55	65041	KH7#17 (OPS 5236)	27 May 1965	V	Agena-D	149 x 267 x 95.8 x 88.7
56	65050	KH7#18 (OPS 6749 + 5501)	25 Jun 1965	V	Agena-D	151 x 283 x 107.6 x 88.8
57	n/a	KH7	12 Jul 1965	V	Agena-D	Failure
58	65058	Vela 5 (OPS 6577) Vela 6 (OPS 6564) ERS 17	20 Jul 1965	C	Agena-D	95000 x 107000 x 35.3 x 5148
59	65062	KH7#19 (OPS 5698 + 6761)	03 Aug 1965	V	Agena-D	149 x 307 x 107.5 x 89.1
60	65076	KH7#20 (OPS 6004)	30 Sep 1965	V	Agena-D	158 x 264 x 95.6 x 88.8
61	n/a	Agena GATV	25 Oct 1965	C	Agena-D	Failure
62	65090	KH7#21 (OPS 8293 + 6232)	08 Nov 1965	V	Agena-D	145 x 277 x 93.9 x 88.7
63	66002	KH7#22 (OPS 7253 + 3179)	19 Jan 1966	V	Agena-D	154 x 246 x 93.9 x 88.5
64	66012	KH7#23 (OPS 1184 + 3011 + 3031)	15 Feb 1966	V	Agena-D	148 x 293 x 96.5 x 89
65	66019	Agena GATV-8	16 Mar 1966	C	Agena-D	285 x 298 x 28.9 x 90.2
66	66022	KH7#24 (OPS 0879 + 0974)	18 Mar 1966	V	Agena-D	152 x 284 x 101 x 88.9
67	66031	OAO 1	08 Apr 1966	C	Agena-D
68	66032	KH7#25 (OPS 0910)	19 Apr 1966	V	Agena-D	145 x 398 x 117 x 89.9
69	66039	KH7#26 (OPS 1950 + 6785)	14 May 1966	V	Agena-D	133 x 358 x 110.6 x 89.4
70	n/a	Agena GATV-9	17 May 1966	C	Agena-D	Failure
	66046	ATDA	01 Jun 1966	C	model	292 x 296 x 28.9 x 90.2
71	66048	KH7#27 (OPS 1577 + 1856)	03 Jun 1966	V	Agena-D	143 x 288 x 87 x 88.9
72	66049	OGO 3	07 Jun 1966	C	Agena-B
73	66051	Midas 08	09 Jun 1966	V	Agena-D
74	66062	KH7#28 (OPS 1850)	12 Jul 1966	V	Agena-D	137 x 236 x 95.5 x 88.3
75	66065	Agena GATV-10	18 Jul 1966	C	Agena-D	290 x 296 x 28.9 x 90.2
76	66073	Lunar Orbiter 1	10 Aug 1966	C	Agena-D	Lunar orbit
77	66074	KH7#29 (OPS 1832 + 6810)	16 Aug 1966	V	Agena-D	146 x 358 x 93.3 x 89.6
78	66077	Midas 09	19 Aug 1966	V	Agena-D
79	66080	Agena GATV-11	12 Sep 1966	C	Agena-D	298 x 298 x 28.8 x 90.3
80	66083	KH7#30 (OPS 1686 + 6874)	16 Sep 1966	V	Agena-D	148 x 333 x 94 x 98.4
81	60089	Midas 10	05 Oct 1966	V	Agena-D
82	66090	KH7#31 (OPS 2055) SGLS 1 (OPS 5345)	12 Oct 1966	V	Agena-D	181 x 258 x 90.9 x 89
83	66098	KH7#32 (OPS 2070 + 5424)	02 Nov 1966	V	Agena-D	159 x 305 x 91 x 89.2
84	66100	Lunar Orbiter 2	06 Nov 1966	C	Agena-D	Lunar orbit
85	66103	Agena GATV-12	11 Nov 1966	C	Agena-D	243 x 310 x 28.8 x 89.9
86	66109	KH7#33 (OPS 1890)	05 Dec 1966	V	Agena-D	137 x 388 x 104.6 x 89.8
87	66110	ATS 1	07 Dec 1966	C	Agena-D
88	67007	KH7#34 (OPS 4399)	02 Feb 1967	V	Agena-D	136 x 357 x 103 x 89.5
89	67008	Lunar Orbiter-3	05 Feb 1967	C	Agena-D	Lunar orbit
90	67031	ATS-2	06 Apr 1967	C	Agena-D	178 x 11124 x 28.4 x 218.9
91	67041	Lunar Orbiter 4	04 May 1967	C	Agena-D	Lunar orbit
92	67050	KH7#35 (OPS 4321 + 5557)	22 May 1967	V	Agena-D	135 x 292 x 91.5 x 88.4
93	67055	KH7#36 (OPS 4360)	04 Jun 1967	V	Agena-D	149 x 456 x 104.9 x 90.6
94	67060	Mariner-5	14 Jun 1967	C	Agena-D	Venus probe
95	67075	Lunar Orbiter 5	01 Aug 1967	C	Agena-D	Lunar probe
96	67111	ATS 3	05 Nov 1967	C	Agena-D
97	68014	OGO 5	04 Mar 1968	C	Agena-D
98	68063	Canyon 1 (OPS 2222)	06 Aug 1968	C	Agena-D	31680 x 39860 x 9.9
99	69036	Canyon 2 (OPS 3148)	13 Apr 1969	C	Agena-D	31680 x 39860 x 9.9
100	70046	Rhyolite 1 (OPS 5346)	19 Jun 1970	C	Agena-D	31680 x 39860 x 9.9
101	70069	Canyon 3 (OPS 7329)	01 Sep 1970	C	Agena-D	31680 x 39860
102	n/a	Canyon 4	04 Dec 1971	C	Agena-D	Failure
103	72101	Canyon 5 (OPS 9390)	20 Dec 1972	C	Agena-D
104	73013	Canyon 6	06 Mar 1973	C	Agena-D	32100 x 39660 x 10.1
105	75055	Rhyolite 2 (OPS 4966)	18 Jun 1975	C	Agena-D	GEO
106	77038	Canyon 7 (OPS 9751)	23 May 1977	C	Agena-D	GEO
107	77114	Rhyolite 3 (OPS 4258)	11 Dec 1977	C	Agena-D	Failure: 146 x 188 x 29.9 x 87.9
108	78038	Rhyolite 4 (OPS 8790)	07 Apr 1978	C	Agena-D	GEO
109	78064	Seasat	26 Jul 1978	V	Agena-D	769 x 799 x 108 x 100.7

Notes: in the launcher date & site column C stands for Cape Canaveral and V for Vandenberg.


Atlas with solid top stage
 Atlas with a solid fuel top stage

Jean-Jacques Serra

Gunter Krebs (listing)

Some Atlas missiles were reconverted in space launchers by addition of solid fuel top stages. OV-1, the first of these programs enabled to orbit two LEO 1.2 tons satellites. The Boeing Burner stage was the only solid top stage capable of control and guidance. The Burner-I was equipped with an Altair engine while the Burner-II featured the Lunar probe Surveyor main engine retro-rocket providing a 4.5-ton thrust. The Burner-IIA was a 2-stage version which second stage had a 4-ton thrust. The Mc Donnell Douglas SGS-II was used for high altitude orbit launches. Thoses stages were made from two 8.6-ton thrust Thiokol Star-48 motors.

First launches were aimed to technological and scientific (OV-1, STP, NTS...) missions. Later on military and civilian payloads were launched for navigation (GPS), ocean surveillance (NOSS) and meteorology (DMSP, NOAA) purposes.

The last launch occured in March 1995 and Titan-2 will take over the launch of those payloads.

Atlas with solid top stage launches [chart 4]

#	Launch id	Payload	Launch date	Type	Status/Comment (orbit in perigee x apogee x inclination x period)
1, 172D	n/a	OV1-1 ABRES 6 (reentry experiment)	21 Jan 1965	D OV1	Failure
2, 68D	n/a	OV1-3	27 May 1965	D OV1	Failure
3, 34D	65078	OV 1-02 SSP 29 (reentry experiment)	05 Oct 1965	D OV1
4, 72D	66025	OV 1-04 OV 1-05	30 Mar 1966	D OV1
5, 58D	66063	OV 1-08 OV1-7	14 Jul 1966	D OV1	Partial failure: OV1-7 didn't reach orbit
6, 89D	66111	OV 1-09 OV 1-10	11 Dec 1966	D OV1
7, 92D	67072	OV 1-11 /1-12 / 1-86	27 Jul 1967	D OV1	Partial failure: OV1-11 didn't reach orbit
8, 107F	68026	OV 1-13 OV 1-14	06 Apr 1968	F OV1
9, 75F	68059	OV1-16 (Spades) OV1-17 (Cannonball 1)	11 Jul 1968	F OV1
10, 7004	n/a	STP, 10 satellites: Orbiscal 1 OV5-8 Gridsphere 1 & 2 Mylar Ballon 1 Rigidsphere 1 & 2 + 3 more	16 Aug 1968	SLV3 Burner2	Failure: the vehicle was destroyed due to a collapse of the payload fairing
11, 104F	69025	OV1-17 OV1-18 OV 1-19 OV1-17A (Orbiscal 2)	18 Mar 1969	F OV1
12, 76F	71067	OV 1-20 OV 1-21 Rigidsphere 1 & 2 Gridsphere 1 & 2 Cannonball 2 Musketball Mylar Balloon	07 Aug 1971	F OV1
13, 102F	72076	STP (Radcat + Radsat)	02 Oct 1972	F Burner2	530 x 750 x 98.4 x 99.5
14, 69F	74054	NTS-1	14 Jul 1974	F PTS	21600 x 22200 x 63 x 720
15, 71F	n/a	STP (P72-2)	12 Apr 1975	F Star-17A	Failure
16, 59F	76038	NOSS 01	30 Apr 1976	F Star-37E
17, 65F	77053	NTS-2	24 Jun 1977	F SGS1	20300 x 20300 x 63 x 720
18, 50F	77112	NOSS 02	08 Dec 1977	F Star-37E
19, 64F	78020	GPS BI-01	22 Feb 1978	F SGS1
20, 49F	78047	GPS BI-02	13 May 1978	F SGS1
21, 47F	78093	GPS BI-03	07 Oct 1978	F SGS1
22, 29F	78096	Tiros N	13 Oct 1978	F Star-37S ISS	846 x 862 x 98.9 x 102
23, 39F	78112	GPS BI-04	11 Dec 1978	F SGS1
24, 27F	79017	Solwind	24 Feb 1979	F OIS
25, 25F	79057	NOAA 06	27 Jun 1979	F Star-37SISS
26, 35F	80011	GPS BI-05	09 Feb 1880	F SGS1
27, 64F	80019	NOSS 03	03 Mar 1980	F Star-37E
28, 34F	80032	GPS BI-06	26 Apr 1980	F SGS1
29, 19F	80043	NOAA B	29 May 1980	F Star-37S ISS
30, 68E	n/a	NOSS 04	08 Dec 1980	E Star-37E	Failure
31, 87F	81059	NOAA 07	23 Jun 1981	F Star-37S ISS
32, 76E	n/a	GPS BI-07	18 Dec 1981	E SGS1	Failure
33, 60E	82118	DMSP/Block-5D2#1	21 Dec 1982	E Star-37S ISS	815 x 828 x 98.8 x 101.2
34, 6001H	83008	NOSS 05	09 Feb 1983	H
35, 73E	83022	NOAA 08	28 Mar 1983	E Star-37S ISS
36, 6002H	83056	NOSS 06	09 Jun 1983	H
37, 75E	83072	GPS BI-08	14 Jul 1983	E SGS2
38, 58E	83113	DMSP/Block-5D2#2	17 Nov 1983	E Star-37S ISS	823 x 835 x 98.7 x 101.4
39, 6003H	84012	NOSS 07	05 Feb 1984	H
40, 42E	84059	GPS BI-09	13 Jun 1984	E SGS2
41, 14E	84097	GPS BI-10	08 Sep 1984	E SGS2
42, 39E	84123	NOAA 09	12 Dec 1984	E Star-37S ISS
43, 41E	85021	Geosat	12 Mar 1985	E OIS	757 x 814 x 108.1 x 100.6
44, 55E	85093	GPS BI-11	09 Oct 1985	E SGS2
45, 6004H	86014	NOSS 08	09 Feb 1986	H
46, 52E	86073	NOAA 10	17 Sep 1986	E Star-37S ISS
47, 6005H	87043	NOSS 09	15 May 1987	H
48, 59E	87053	DMSP B5D2-3	20 Jun 1987	E Star-37S ISS
49, 54E	88006	DMSP/Block-5D2#4	03 Feb 1988	E Star-37S ISS	820 x 830 x 98.7 x 101.5
50, 63E	88089	NOAA 11	24 Sep 1988	E Star-37S ISS
51, 28E	90031	Stacksat/P87-2 (3)	11 Apr 1990	E Altair-3	760 x 780 x 90 x 100
52, 61E	90105	DMSP/Block-5D2#5	01 Dec 1990	E Star-37S ISS	730 x 850 x 98.9 x 100.7
53, 50E	91032	NOAA 12	14 May 1991	E Star-37S ISS
54, 53E	91082	DMSP/Block-5D2#6	28 Nov 1991	E Star-37S ISS	840 x 860 x 98.9 x 102
55, 34E	93050	NOAA 13	09 Aug 1993	E Star-37S ISS
56, 20E	94057	DMSP B5D2-7	29 Aug 1994	E Star-37S ISS
57, 11E	94089	NOAA 14	30 Dec 1994	E Star-37S ISS
58, 45E	95015	DMSP B5D2-8	24 Mar 1995	E Star-37S ISS

Notes: All launches from Vandenberg.


 Atlas Centaur

Jean-Jacques Serra

Gunter Krebs (listing)

The Atlas Centaur launchers are the most powerful versions in the Atlas familly and the only to be used since 1995. They use the Centaur top-stage which was the first cryogenic rocket stage.

The Pratt & Whitney RL10 engine consuming liquid oxygen and hydrogen had a long and difficult development (see chart 5). Its design started in 1958. It first flew in 1962 but didn't launch a real payload before 1966. The Centaur stage was designed to be used by Atlas. It had the same diameter and was 9.1 m long. In its operational version it was equipped with two RL10 A-3-3 engines with a thrust of 6.8 tons each.

In the late-70ies the total height of the Atlas Centaur reached 40 m (originally 34 m) and its mass at launch increased from 132 to 150 tons. At this time the launch program was to be abandonned since NASA had decided to transfer all launches to the Shuttle. In fact STS was less available than expected and the Atlas launch program was resumed with a simplified motor: the RL10 A-3-3A with 7.5 tons thrust which first flew in 1984.

Evolution of Centaur's propulsion system [chart 5]

Designation	First launch	Main engine Thrust (t.)	Main engineSI (sec.)	Applications
RL10 A-1	1962	6.8	425	Tests
RL10 A-3-1	1963	6.8	431	Atlas Centaur
RL10 A-3-3	1966	6.8	444	Atlas Centaur
RL10 A-3-3A	1984	7.5	446	Atlas-1 & -2
RL10 A-4	1991	9.4	449	Atlas-2A & -2AS

During its first activity period (see chart 6) the Atlas Centaur launched:

- probes to the Moon (Surveyor) and to other planets (Marnier, Pioneer)

- heavy scientific satellites (OAO, HEAO)

- geostationary telecommunication satellites (ATS, Intelsat, Comstar, Fleetsatcom)

In 1987 the augmented Atlas Centaur was selected by the USAF as the MLV2 standard launcher. This new launcher is refered to as Atlas-2 and the former version as Atlas-1. The basic Atlas-2 is an Atlas Centaur which has a 2.7 m longer first stage and a 0.9 m longer second stage. Furthermore the first stage is equipped with the new MA-5A motors. Atlas-2A is different by its second stage RL10 A-4 engines with deployable nozzle. Those rockets range from 45.6 to 47.5 m high and weigh 187 tons (Atlas-1 was 42-44 m high and weigh 164 tons).

Atlas-2AS is still more powerful. It is made from Atlas-2A to which two pairs of Castor-4A boosters of 44.2 tons thrust each are added. Each pair ignites one after the other. Thus Atlas-2A weighs 234 tons and can deliver 3.6 tons in GTO compared to 2.7 and 2.9 tons for Atlas-2 and -2A, and 2.3 tons for Atlas-1.

Atlas Centaur rockets are optimized for geostationary orbit satellites.

Atlas Centaur launches [chart 6]

#	Launch id	Payload	Launch Date	Site	Type	Status/Comment (orbit in perigee x apogee x inclination x period)
1, AC001	n/a	suborbital test	08 May 1962	C	LV3C C-D	Failure because of collapse of payload shroud
2, AC002	63047	test	27 Nov 1963	C	LV3C C-D	544 x 1699 x 30.3 x 170.5
3, AC003	n/a	test	30 Jun 1964	C	LV3C C-D	Hydraulic failure in Centaur
4, AC004	64082	test (Surveyor Mass Model 1)	11 Dec 1964	C	LV3C C-D	165 x 178 x 30.7 x 87.8
5, AC005	n/a	Surveyor SD 1	02 Mar 1965	C	LV3C C-D	Failure: exploded on launch pad
6, AC006	65064	Surveyor SD 2	11 Aug 1965	C	LV3C C-D	Solar orbit
7, AC008	66030	test (Surveyor Mass Model 2)	08 Apr 1966	C	LV3C C-D	175 x 334 x 30.7 x 89.5
8, AC010	66045	Surveyor-1	30 May 1966	C	LV3C C-D	Payload landed on the Moon
9, AC007	66084	Surveyor-2	20 Sep 1966	C	LV3C C-D	Payload impacted on the Moon
10, AC009	66095	test (Surveyor Mass Model 3)	26 Oct 1966	C	LV3C C-D	200 x 47000 x 22.9
11, AC012	67035	Surveyor-3	17 Apr 1967	C	LV3C C-D	Payload landed on the Moon
12, AC011	67068	Surveyor-4	14 Jul 1967	C	LV3C C-D	Payload impacted on the Moon
13, AC013	67084	Surveyor-5	08 Sep 1967	C	SLV3C C-D	Payload landed on the Moon
14, AC014	67112	Surveyor-6	07 Nov 1967	C	SLV3C C-D	Payload landed on the Moon
15, AC015	68001	Surveyor-7	07 Jan 1968	C	SLV3C C-D	Payload landed on the Moon
16, AC017	68068	ATS-4	10 Aug 1968	C	SLV3C C-D	Failure: Centaur failed on second ignition
17, AC016	68110	OAO 2	07 Dec 1968	C	SLV3C C-D
18, AC020	69014	Mariner-6	25 Feb 1969	C	SLV3C C-D	Mars probe
19, AC019	69030	Mariner-7	27 Mar 1969	C	SLV3C C-D	Mars probe
20, AC018	69069	ATS 5	12 Aug 1969	C	SLV3C C-D
21, AC021	n/a	OAO 3	30 Nov 1970	C	SLV3C C-D	Failure: payload shroud failed to seperate
22, AC025	71006	Intelsat 402	26 Jan 1971	C	SLV3C C-D
23, AC024	n/a	Mariner-8	08 May 1971	C	SLV3C C-D	Failure: Centaur guidance failure
24, AC023	71051	Mariner-9	30 May 1971	C	SLV3C C-D	Mars probe
25, AC026	71116	Intelsat 403	20 Dec 1971	C	SLV3C C-D
26, AC028	72003	Intelsat 404	23 Jan 1972	C	SLV3C C-D
27, AC027	72012	Pioneer-10	03 Mar 1972	C	SLV3C C-D Star-37E	Jupiter probe
28, AC029	72041	Intelsat 405	13 Jun 1972	C	SLV3C C-D
29, AC022	72065	OAO 3	21 Aug 1972	C	SLV3C C-D
30, AC030	73019	Pioneer-11	06 Apr 1973	C	SLV3D C-D1A Star-37E	Jupiter & Saturn probe
31, AC031	73058	Intelsat 407	23 Aug 1973	C	SLV3D C-D1A
32, AC034	73085	Mariner-10	03 Nov 1973	C	SLV3D C-D1A	Venus and Mercury probe
33, AC032	74073	Intelsat 408	21 Nov 1974	C	SLV3D C-D1A
34, AC033	n/a	Intelsat 406	20 Feb 1975	C	SLV3D C-D1A	Failure: 1st stage failes due to electrical shortcut
35, AC035	75042	Intelsat 401	22 May 1975	C	SLV3D C-D1A
36, AC036	75091	Intelsat 4A01	26 Sep 1975	C	SLV3D C-D1AR
37, AC037	76010	Intelsat 4A02	29 Jan 1976	C	SLV3D C-D1AR
38, AC038	76042	Comstar 1	13 May 1976	C	SLV3D C-D1AR
39, AC040	76073	Comstar 2	22 Jul 1976	C	SLV3D C-D1AR
40, AC039	77041	Intelsat 4A04	26 May 1977	C	SLV3D C-D1AR
41, AC045	77075	Heao 1	12 Aug 1977	C	SLV3D C-D1AR
42, AC043	n/a	Intelsat 4A05	30 Sep 1977	C	SLV3D C-D1AR	Failure: Atlas boostersection turbopump failed
43, AC046	78002	Intelsat 4A03	07 Jan 1978	C	SLV3D C-D1AR
44, AC044	78016	Fleetsatcom 1	09 Feb 1978	C	SLV3D C-D1AR
45, AC048	78035	Intelsat 4A06	31 Mar 1978	C	SLV3D C-D1AR
46, AC050	78051	Pioneer-12 (Pioneer Venus-1)	20 May 1978	C	SLV3D C-D1AR	Probe to Venus, Venus orbit
47, AC048	78068	Comstar 3	29 Jun 1978	C	SLV3D C-D1AR
48, AC051	78078	Pioneer-13 (Pioneer Venus-2)	08 Aug 1978	C	SLV3D C-D1AR	Probe to Venus: soil module
49, AC052	78103	Heao 2	13 Nov 1978	C	SLV3D C-D1AR
50, AC047	79038	Fleetsatcom 2	04 May 1979	C	SLV3D C-D1AR
51, AC053	79082	Heao 3	20 Sep 1979	C	SLV3D C-D1AR
52, AC049	80004	Fleetsatcom 3	18 Jan 1980	C	SLV3D C-D1AR
53, AC057	80087	Fleetsatcom 4	31 Oct 1980	C	SLV3D C-D1AR
54, AC054	80098	Intelsat 502	06 Dec 1980	C	SLV3D C-D1AR
55, AC042	81018	Comstar 4	21 Feb 1981	C	SLV3D C-D1AR
56, AC056	81050	Intelsat 501	23 May 1981	C	SLV3D C-D1AR
57, AC059	81073	Fleetsatcom 5	06 Aug 1981	C	SLV3D C-D1AR
58, AC055	81119	Intelsat 503	15 Dec 1981	C	SLV3D C-D1AR
59, AC058	82017	Intelsat 504	04 Mar 1982	C	SLV3D C-D1AR
60, AC060	82097	Intelsat 505	28 Sep 1982	C	SLV3D C-D1AR
61, AC061	83047	Intelsat 506	19 May 1983	C	SLV3D C-D1AR
62, AC062	84057	Intelsat 509	09 Jun 1984	C	G C-D1AR	Partial failure: Centaur LOX-tank exploded on LEO
63, AC063	85025	Intelsat 510	22 Mar 1985	C	G C-D1AR
64, AC064	85055	Intelsat 511	30 Jun 1985	C	G C-D1AR
65, AC065	85087	Intelsat 512	29 Sep 1985	C	G C-D1AR
66, AC066	86096	Fleetsatcom 7	05 Dec 1986	C	G C-D1AR
67, AC067	n/a	Fleetsatcom 6	26 Mar 1987	C	G C-D1AR	Failure because of lightning strike
68, AC068	89077	Fleetsatcom 8	25 Sep 1989	C	G C-D1AR
69, AC069	90065	CRRES	25 Jul 1990	C	1	330 x 33600 x 18.1 x 591
70, AC070	n/a	Yuri 3H (BS 3H)	19 Apr 1991 at 23:30 UT	C	1	Failure: one of the two Centaur engines didn't ignite
71, AC102	91083	Eutelsat 2F3	07 Dec 1991 at 22:47 UT	C	2 (8102)
72, AC101	92006	DSCS 3-05	11 Feb 1992 at 00:41 UT	C	2 IABS
73, AC072	92013	Galaxy 5	14 Mar 1992	C	1
74, AC105	92032	Intelsat K	10 Jun 1992 at 00:00 UT	C	2A
75, AC103	92037	DSCS 3-06	02 Jul 1992 at 21:54 UT	C	2 IABS
76, AC071	n/a	Galaxy 1R failure	22 Jul 1992	C	1	Failure: 3rd stage failed to ignite
77, AC074	93015	UHF 1	25 Mar 1993 at 22:48 UT	C	1	Partial failure
78, AC104	93046	DSCS 3-07	19 Jul 1993	C	2 IABS
79, AC075	93056	UHF 2	03 Sep 1993 at 11:17 UT	C	1
80, AC106	93074	DSCS 3-08	28 Nov 1993	C	2 IABS
81, AC108	93077	Telstar 401	16 Dec 1993 at 00:40 UT	C	2AS
82, AC073	94022	Goes 8	13 Apr 1994 at 06:44 UT	C 36B	1
83, AC076	94035	UHF 3	24 Jun 1994 at 13:50 UT	C 36B	1
84, AC107	94047	DBS 2	03 Aug 1994 at 23:57 UT	C 36A	2A
85, AC111	94064	Intelsat 703	06 Oct 1994 at 06:35 UT	C 36B	2AS
86, AC110	94079	Orion 1	23 Nov 1994 at 10:21 UT	C 36A	2A
87, AC113	95001	Intelsat 704	10 Jan 1995 at 06:18 UT	C	2AS
88, AC112	95003	UHF 4	29 Jan 1995 at 01:25 UT	C	2
89, AC115	95013	Intelsat 705	22 Mar 1995 at 06:18 UT	C 36B	2AS
90, AC114	95019	AMSC 1	07 Apr 1995 at 23:47 UT	C 36A	2A
91, AC077	95025	Goes 9	23 May 1995 at 05:52 UT	C 36B	1
92, AC116	95027	UHF 5	31 May 1995 at 15:27 UT	C 36A	2
93, AC118	95038	DSCS 3-09	31 Jul 1995 at 23:30 UT	C	2A IABS
94, AC117	95043	Jcsat 3	29 Aug 1995 at 00:53 UT	C 36B	2AS
95, AC119	95057	UHF 6	22 Oct 1995 at 08:00 UT	C 36B	2
96, AC121	95065	Soho	02 Dec 1995 at 08:08 UT	C 36B	2AS
97, AC120	95069	Galaxy 3R	15 Dec 1995 at 00:23 UT	C 36A	2A
98, AC126	96006	Palapa C1	1 Fab 1996 at 01:15 UT	C 36B	2AS

Note: In the launch site column C stands for Cape Canaveral and may be followed by the launch pad number. In the type column the second part of the type beginning with C- stands for Centaur-


Atlas

[launch vehicle index]

Origins of Atlas

Atlas without top stage

Atlas with an Agena stage

Atlas with solid top stage

Atlas Centaur

AC070

AC074


 Atlas AC070

General

Launch date	19 Apr 1991 at 23:30 UT
Launch site	Cape Canaveral
Type	1
Payload mass	1115 kg
Payload	Yuri 3H
Failure cause	one of the two Centaur engines didn't ignite


 Atlas AC074

General

Launch id	93015
Launch date	25 Mar 1993 at 22:48 UT
Launch site	Cape Canaveral LC36
Type	1
Payload mass	~3000 kg
Payload	A: UHF 1

The Atlas lost some power during the booster burn, and the Centaur had to burn longer to make up and get into parking orbit. As a result, the second Centaur burn to transfer orbit ran out of fuel during the burn. The payload satellite was left in a 219 x 9158 km x 27.3 deg orbit.

This was the third failure of the Atlas 1 class rocket in the last 4 launches!


 Black Arrow

Jean-Jacques Serra

Gunter Krebs (listing)

Origin: Black Knight experimental rocket

In 1957 the UK Royal Aircraft Establishment began the development of the Black Knight rocket to study atmosphere reentry of ballistic warheads.

The Black Knight was a long cylinder surmounted by a conical rounded head with 4 ribs equipped of stabilization rockets. It was powered by a Gamma 301 made by Bristol Siddeley; its thrust increased from 74 to 106 kN. On its first launch at Woomera in September 1958 it broke the world altitude record with 564 km. It was fired 22 times successfuly between 1958 and 1965.

Black Arrow

The development of the space launcher Black Arrow began in 1964 under direction of the Royal Aircraft Establishment. It was 3-stage rocket of only 13 m high weighing 18.1 tons at takeoff time with a LEO payload capacity of nearly 100 kg.

The first stage weighed 14.1 tons and measured 5.9 m high for 2  diameter. It was equipped with a Gamma-8 motor that featured 8 combustion chambers (deployable nozzles). It fired during 125 seconds providing 218 kN thrust and 251 kN in vacuum. Second stage was 3.55 m high per 1.37 m diameter and weighed 3.5 tons. Its Gamma-2 motor featuring 2 combustion chambes (deployable nozzles) consummed the same propellant and delivered 69 kN thrust during 120 seconds. The third stage was underthe 1.37 m diameter cap and layed on a spinning table. It was 1.3 m high, 71 cm diameter and 0.5 t weight. This stage was powered by a Waxwing solid fuel motor providing a mean thrust of 21 kN over 40 seconds.

The first ballistic flight which occured in Jun 1969 failed but the second in March 1970 was successful. The first orbiting attempt failed in Sep 1970 when second stage shutdown 13 seconds early. In July 1971 the British government decided to drop the national program although one flight was still to be carried out. Nonetheless it was fired in Oct 1971 and orbited the Prospero satellite.

Black Arrow launches

#	Launch id	Payload	Launch Date	Site	Type	Status/Comment
1	n/a	Ballistic flight	29 Jun 1969	W	2-stage	Failure: control lost after 50 s
2	n/a	Ballistic flight	04 Mar 1970	W	2-stage
3	n/a	Orba (X2)	02 Sep 1970	W		Failure: 2nd stage produced unsufficient thrust
4	71093	Prospero (X3)	28 Oct 1971	W

Notes: All launches from Woomera Rocket Range in Australia


 Conestoga

American launcher program built by E.E.R. Systems of Seabrook, Md.

The Conestoga uses a Castor 4B first stage core with Castor 4A and Castor 4B strapons, and a Star 48V upper stage.


Conestoga

[launch vehicle index]

Conestoga 01


 Conestoga 01

General

Launch id	n/a
Launch date	23 Oct 1995 at at 22:03 UT
Launch site	Wallops LA0
Type	Conestoga 1620
Payload mass
Payload	Meteor (US)
Failure cause

The vehicle was destroyed 45s into the first stage burn, at an altitude of 11 km.


 Diamant

Jean-Jacques Serra

Gunter Krebs (listing)

Origin: Pierre Précieuses (precious stones) experimental rocket series

The SEREB (Société pour l'Etude et la Réalisation d'Engins Balistiques, firm for the study and developpement of ballistic missiles) was founded in 1959 to support the DMA missile department which was in charge of the French strategic ballistic missile programs SSBS and MSBS. Work begin by a ballistic study program to acquire the technology necessary to development of such missiles. This program achieved several carriers in the Pierre Précieuses series: Agate, Topaze, Emeraude and Saphir.

The VE-110 Agate was the first of the series. It was a 1-stage solid-fuel (Isolane) non piloted carrier of 80 cm diameter. The VE-111 Topaze was similar to Agate but guided by 4 rotative nozzles. The VE-121 Emeraude was 1.40 m diameter; it was the first is the series to use liquid propellant (nitric acid and turpentine). The VE-231 Saphir had 2 stages: Emeraude + Topaze. Saphir enabled in-flight experiments of cap release, stage separation, inertial guidance and reentry.

In December 1961 it was decided to build the Diamant launcher by replacing the payload of Saphir by a third stage. In May 1962 CNES selected DMA to manage the Diamant program, SEREB being the prime contractor. The Rubis rocket was designed to test the third stage in-flight, on top of an Agate stage.

Diamant A

The diamant A launcher was made of a 10 m high, 1.4 m diameter Emeraude first stage weighing 14.7 tons. Its Vexin LRBA directional-nozzle motor burned during 93 seconds and delivered 269 kN thrust at sea level (304 kN in vacuum). The second stage was Topaze: 4.7 m high per 80 cm diameter and weighed 2.9 tons. It provided a mean thrust of 156 kN during 44 seconds. The P064 third stage was 2 m high and 65 cm diameter. It weighed 709 kg including 640 kg Isolane (thus its name). It burned for 45 seconds providing 27 to 53 kN thrust. With its cap Diamant was 18.95 m high and weighed 18.4 tons.

Diamant achieved orbiting at first try on 26 Nov 1965. The payload was the simple technological capsule Astérix. After this launch the 3 remaining rockets were used to orbit geodesy satellites (D1 program) between Feb 1966 and Feb 1967. All launches were carried out from the CIEES (Centre InterArmées d'Essais d'Engins Spéciaux, inter-army special machine test center) in Sahara which was closed in July 1967.

Once the Diamant A program ended Rubis was still used as sounding rocket: in July 1967 it delivered an experiment of the Paris-Meudon observatory's space radioastronomy department at 1560 km altitude. The third stage of Diamant A was then used twice as top stage of the Tibère launcher for the Electre experiments between Feb 1971 and Mar 1972.

Diamant B

After Diamant numerous projects appear but CNES decides to built a launcher directly derived from Diamant A. The main evolution was the lengthened first stage which used more energy-providing propellants. This first stage called Améthyste was 14.2 m high, 1.4 m diameter, and 20.1 t weight. Its Valois motor delivered 316 kN thrust at sea level (400 kN in vacuum) during 116 seconds. The second stage was identical the Diamant A's one; The top stage (P068) was also enhanced: 1.67 m high, 80 cm diameter and 50 kN thrust during 46s. With its cap (85 cm diameter instead of 65 cm for Diamant A) Diamant B was 23.5 m high and weighed 24.6 tons.

Six Diamant B were ordered: 2 for CNES and 4 for ELDO (in single stage version) which were to be used to test the PAS (Perigee-Apogee System) for Europa 2. Finaly ELDO dropped the idea and the 5 rocket built were used by CNES.

After the launch of the German Wika technological capsule Diamant B launched Peole (technology) and Tournesol (astronomy). The last 2 launches were failures. All launches occured from the CSG (Centre Spatial Guyanais, Guyana space center) which is operational since April 1968 when the first sounding rocket Veronique was launched.

Diamant BP4

Development of Diamant BP4 started in Jan 1972. It was based on the first and third stage of its ancestor. The new second stage P4 (Rita) was from the ballistic missile MSBS guided by jet deviation (freon injection). It was 2.28 m long and 1.5 m diamter; it provided a mean 180 kN thrust during 55 seconds. With the 1.38 m cap from the Black Arrow program Diamant BP4 was 21.6 m high and weighed 27 tons.

After 1975 France stopped its sounding rocket and national launcher programs to devote entirely to the european Ariane launcher.

Diamant launchers evolution

Designation	First launch	1st stage	2nd stage	3rd stage	300 km	500 km	1000 km
A	1965	Emeraude	Topaze	P064		80
B	1970	Amethyste	Topaze	P068	160	115	25
BP4	1975	Amethyste	Rita	P068	200	153	45
Diamant launches

#	Launch id	Payload	Launch Date	Site	Type	Status/Comment
1	65096	Asterix	26 Nov 1965	H	A
2	66013	Diapason	17 Feb 1966	H	A
3	67011	Diadème 1	08 Fab 1967	H	A	Partial failure: orbit too low
4	67014	Diadème 2	15 Feb 1967	H	A
5	70017	A: Dial-Wika B: Mika	10 Mar 1970	K	B
6	70109	Péole	12 Dec 1970	K	B
7	71030	Tournesol	15 Apr 1971	K	B
8	n/a	Polaire	5 Dec 1971	K	B	Failure: 2nd stage failed
9	n/a	Castor Pollux	22 May 1972	K	B	Failure: 3rd stage failed
10	75010	Starlette	6 Feb 1975	K	BP4
11	75039	A: Pollux B: Castor	17 May 1975	K	BP4
12	75092	Aura	27 Sep 1975	K	BP4

Notes: Launch site: H for Hammaguir, Algeria; K for Kourou


 H2

Japanese launcher operated by NASDA

2-stage rocket


H2

[launch vehicle index]

H2 01

H2 02


 H2 01

General

Launch id	94007
Launch date	3 Feb 1994 at 22:20 UT
Launch site	Tanegashima
Type
Payload mass
Payload	A: Ryusei B: Myojo


 H2 02

General

Launch id	95011
Launch date	17 Mar 1995 at 08:01 UT
Launch site	Tanegashima
Type
Payload mass
Payload	A: SFU B: GMS 5

This launch introduces two solid sub-boosters to increase it's capacity


 ISAS launchers

Jean-Jacques Serra

While developping new 2-stage sounding rockets of the Kappa series the TODAI decided in the early sixties to design 3-stage rockets named Lambda. The most powerful Kappa rockets (9 & 10) weighed 1.5 to 1.7 tons and had 42 cm base stages. Lambda-3 had a 73 cm diameter first stage and weighed over 7 tons. For the International Quiet Sun Year (IQSY) of 1964-65 those launchers performed 1000 km altitude orbit with 100 kg payload.

Lambda-4S

In 1965 the TODAI started developping a satellite launcher derived from the Lambda-3 sounding rocket which in its most powerful configuration (Lambda-3H) was able to orbit 100 kg at 2000+ km. This launcher was achieved by adding a fourth stage and solid fuel boosters to Lambda-3.

Four orbit injection attempts were made in Sep & Dec 1966, Apr 1967 and Sep 1969. Those launches occured from Uchinoura (31.2° North, 130.6° East) near Kagoshima on the Kyushu island. Finaly success occured in 1970.

This first Japanese launcher named Lambda-4S was 16.5 m high, weighed 9.5 tons and burned only solid fuel. The first stage was 73 cm in diameter and provided 26 tons thrust during 28 seconds. It was assisted during the first 7 seconds by 2 solid fuel boosters of 26 tons thrust. The second stage (same diameter) provided 12 t thrust during 28 seconds. The third stage was 50 cm in diameter; it was capable of 6.5 t thrust during 27 seconds. The top stage was made of a 113 kg powder bloc providing 0.8 ton thrust during 27 seconds which spherical shield made up the satellite's structure. The latter was only a technological capsule which mass at burn shutdown didn't exceed 23 kg. The vehicle was launched from an inclined ramp. It wasn't piloted; a gyroscopic system only controled the fourth stage's altitude before ignition after the ballistic phase (which follows the third stage shutdown).

On 11 Feb 1970 the Lambda-4S number 5 orbited the first capsule named Ohsumi at 351 km x 5142 km x 31.2°. This is the only object launched by a Lambda rocket... because it was abandonned as a space launcher.

Mu series rockets

Seven months after the successful Lambda-4S orbiting the Japanese fired the first model of a new launcher. The Mu-4S kept the same technology but had much greater performances. It was 23.6 m high, 43.6 tons in weight and could put a 100 kg payload in a 31°, 500 km circular orbit.

It's first stage was 1.41 m in diameter and thrusted 85 tons during 61 seconds. It was assisted by eight 13 tons thrust boosters during the first 5.5 seconds of the flight. The second stage had the same diameter whereas the third was 86 cm and while the 77 cm fourth stage supported a 79 cm diameter cap. The respective thrusts were: 29, 13 and 2.7 tons. The guidance system remained simplistic: only the fourth stage was piloted by jet deviation.

After a failure in September 1970 for the first flight, Mu-4S succeeded the 3 next attempts between Feb 1971 and Aug 1972.

In 1974 a new version of Mu with only 3 stages was introduced. This launcher named Mu-3C was equipped with the old first stage and boosters. The second stage was modified and equipped with a radio-inertial guidance which controlled a jet deviation piloting device (freon injection) and a roll control using lateral propellers. This stage provided 35 tons thrust during 55 seconds. The third stage was inherited from Mu-4S fourth stage; it had 6.6 tons thrust capability during 45 seconds. It was also under the 1.41 m diameter fuse cap.

This 41.6 t launcher with its 20.2 m height had similar performances to Mu-4S although lowerer at high altitude. It was used 4 times between Feb 1974 and Feb 1979; 3 launches were successful.

A more powerful launcher appeared in 1977: Mu-3H. The first stage was longer than the former one: its solid fuel engine (27 tons) provided 110 t thrust during 56 seconds. The cap had been lengthened and could host a fourth stage to reach very elliptical orbits.

Mu-3H was 23.8 m high for 48.7 tons at takeoff. It could orbit 100 kg at 700 km in the 3-stage version and more twice as much in the 4-stage version. It was used 3 times with success between Feb 1977 and Feb 1979 including a launch with 30500 km apogee orbit.

The fourth version of the launcher, Mu-3S, only differed from the former vehicle by the addition of a piloting system to the first stage. It was based on a nozzle freon injection device and on a roll control system provided by 4 gas generators fixed at the end of the 4 empannages. The vehicle had the same performances as Mu-3H performances. It was used to launch 4 satellites between Feb 1980 and Feb 1984.

The next version was Mu-3S2; it was complety modified, only the first stage remained the same. The number of boosters was brought back to two but they mesured 74 cm in height and 29 tons in thrust (31 seconds duration). The second stage was lenghtened; it provided 50 tons thrust during 52 seconds. The third stage's diameter was increased to 1.41 m; it provided 11 tons thrust during 82 seconds. The launchers reached 61.2 tons in mass and 27.2 m in height. The orbitable payload which took place in an enlarged cap of 1.65 m diameter was almost twice as heavy as for Mu-3S1: 680 kg at 31°, 250 km altitude.

Mu-3S2 was used 8 times (1 failure) between Jan 1985 and Jan 1995. It launched 2 interplanetary probes to the Moon and to the Halley comet.

Mu launches

#	Launch id	Payload	Launch date	Type	Status/Comment (orbit in perigee x apogee x inc. x period)
1	n/a	MS-F1	25 Sep 1970	Mu-4S	Failure (61 kg)
2	71011	Tansei 1 (MS-T1)	16 Feb 1971	Mu-4S
3	71080	Shinsei (MS-F2)	28 Sep 1971	Mu-4S
4	72064	Denpa (REXS)	19 Aug 1972	Mu-4S
5	74008	Tansei 2 (MS-T2)	16 Feb 1974	Mu-3C
6	75014	Taiyo (SRATS)	24 Feb 1975	Mu-3C
7	n/a	Corsa A	04 Feb 1976	Mu-3C	Failure (86 kg)
8	77012	Tansei 3 (MS-T3)	19 Feb 1977	Mu-3H	824 x 3932 x 65.8 x 134.3
9	78014	Kyokko (Exos A)	04 Feb 1978	Mu-3H
10	78087	Jikiken (Exos B)	16 Sep 1978	Mu-3H
11	79014	Hakucho (Corsa B)	21 Feb 1979	Mu-3C
12	80015	Tansei 4 (MS-T4)	17 Feb 1980	Mu-3S1
13	81017	Hinotori (Astro A)	21 Feb 1981	Mu-3S1
14	83011	Tenma (Astro B)	20 Feb 1983	Mu-3S1
15	84015	Ohzora (Exos C)	14 Feb 1984	Mu-3S1
16	85001	Sakigake/MS-T5	07 Jan 1985	Mu-3S2	probe to Halley comet (138 kg)
17	85073	Suisei/PLANET-A	18 Aug 1985	Mu-3S2	probe to Halley comet (140 kg)
18	87012	Ginga (Astro C)	05 Feb 1987	Mu-3S2
19	89016	Akebono (Exos D)	21 Feb 1989	Mu-3S2
20	90007	Hiten (MUSES-A) Hagoromo	24 Jan 1990	Mu-3S2	Probe to the Moon (193 kg)
21	91062	Yohkoh (Solar A)	30 Aug 1991	Mu-3S2
22	93011	Asuka (Astro D)	20 Feb 1993	Mu-3S2
23	n/a	EXPRESS	15 Jan 1995	Mu-3S2	Partial failure

Note: All launches from Kagoshima


ISRO launchers
 ISRO vehicles

Jean-Jacques Serra

Gunter Krebs (listing)

Indian founded its space agency ISRO in 1969 and then a Ministry of Space in 1972. The next step was to decide to build a national space launcher.

SLV 3 (Satellite Launch Vehicle) and ASLV (Advanced SLV)

SLV 3 was a 4-stage solid-fuel light launcher (polybutadiène). It was 17.8 tons and 22.7 m high with a 1 m diameter max. Its payload mass in circular 500 km orbit was around 40 kg.

The first stage was 9 m high; it delivered 420 kN t (sea level) thrust during 53 seconds. The second stage (80 cm diameter) operated during 42 seconds and provided 200 kN thrust. The third stage (same diameter as stage 2) was fired for 46 seconds and delivered over 60 kN thrust. The 4th stage (65 cm diameter) was fired for 30 seconds and provided about 22 kN thrust. Two ballistic phases occured during the flight: one after second stage shutdown (until 88 km altitude) and after third stage shutdown (to reach perigee altitude).

Rockets were launched from the Sriharikota base on the Indian East coast. This site is operational since the success of a RH-125 sounding rocket in October 1971. After a first attempt which failed in August 1979 the SLV 3 rocket orbited 3 little Rohini scientific satellites in July 1980, Mai 1981 and April 1983. Then the launcher was abandonned for the ASLV.

ASLV was dirived from SLV 3 by the addition of two boosters which dimensions and performances were similar to those of the first stage. Those boosters provided the takeoff of the vehicle by providing each 440 kN thrust during 49 seconds. This caused the first stage to be modified to operate in the air. ASLV was 24 m high and its capacity reached 150 kg payload in LEO (40 km).

The first two launches were failures in March 1987 and July 1988. Then ASLV orbited two SROSS satellites in May 1992 and May 1994.

Noticeable is tha fact the the first stage of the SLV 3 was used from 1989 on as first stage of the experimental Agni IRBM (2500 km range). This is perhaps a unique example of transfert of a civilian stage to a military application.

PSLV (Polar Satellite Launch Vehicle)

PSLV is a 4-stage launcher measuring 44 m high for 2.8 m diameter max, weighing 275 tons.It can orbit around 1 ton payload in sun-synchronous polar orbit.

The first stage is 20 h high and weighs 129 tons. It is powered by a solid fuel motor (HTPB: Hydroxyl-Terminated PolyButadiène) which burns during 100 seconds and provides 3500 kN thrust at sea level (4600 kN in vacuum). It is supported by 6 boosters --switched on by group of two then four-- derived from the SLV 3 and ASLV first stage. Each of those deliver 440 kN thrust at sea level (660 kN in vacuum). The second stage is 11 m high for 2.8 m diameter and weighs 38 tons. Its Vikas motor --built under French SEP licence-- consumes liquid propellant (peroxyde d'azote and UDMH: Unsymmetrical DiMethylHydrazine). It provides 725 kN thrust during 150 seconds. The third stage is 3.5 m high and 2 m diameter; it weighs 7 tons. Its solid fuel motor (HTPB) provides 340 kN thrust. The fourth stage protected by a bulb cap is 2.6 m long by 1.34 m diameter. It is propulsed by 2 ergols motors (peroxyde d'azote and MMH: MonoMethylHydrazine) of 7.5 kN thrust each which burn during about 7 minutes.

The first launch failed in Sep 1993 because of a software problem in the guidance system. The second launch in Oct 1994 orbited IRS P2. The next flights are scheduled every 12 to 18 months for the IRS remote sensing satellites.

SLV 3 launches

#	Launch id	Payload	Launch date	Type	Status (orbit in perigee x apogee x inc. x period)
1	n/a	Rohini 1A	10 Aug 1979	SLV 3	Failure
2	80062	Rohini 1B	18 Jul 1980	SLV 3
3	81051	Rohini 2	31 May 1981	SLV 3	Partial failure
4	83033	Rohini 3	17 Apr 1983	SLV 3

Notes: All launches from Sriharikota

ASLV launches

#	Launch id	Payload	Launch date	Type	Status (orbit in perigee x apogee x inc. x period)
1, D1	n/a	Sross 1	24 Mar 1987	ASLV	Failure
2, D2	n/a	Sross 2	12 Jul 1988	ASLV	Failure
3, D3	92028	Sross 3	20 May 1992	ASLV	Partial failure
4, D4	94027	Sross C2	4 May 1994 at 00:00 UT	ASLV

Notes: All launches from Sriharikota

PSLV launches

#	Launch id	Payload	Launch date	Type	Status (orbit in perigee x apogee x inc. x period)
1, D1	n/a	IRS 1E	20 Sep 1993 at 00:12 UT	PSLV	Failure: computer error
2, D2	94068	IRS P2	15 Oct 1994 at 05:07 UT	PSLV
3, D3	96017	IRS P3	21 Mar 1996 at 04:53 UT	PSLV

Notes: All launches from Sriharikota


 LLV

Lockheed-Martin Launch Vehicle

3-stage launcher capable of carrying payloads of up to one ton designed by Lockheed Martin's Missiles and Space division in Sunnyvale, Calif.

The rocket is made of a Castor 120 first stage, an Orbus 21D second stage, and an OAM Orbit Adjust Module hydrazine third stage.

Lockheed Martin has an agreement with the US Air Force to launch as many as 10 of the rockets over the next 15 years.


LLV

[launch vehicle index]

LLV 01


 LLV 01

General

Launch date	15 Aug 1995
Launch site	Vandenberg SLC6
Type	2-stage
Payload mass	150 kg
Payload	Gemstar
Failure cause	destroyed on command 160 seconds after launch

The first stage separated on time, but the rocket started oscillating toward the end of first stage flight.


Long March

Launcher operated by Great Wall Industry, China

  Chinese CZ-2E and CZ-3 geostationary class launches

CZ3   1984 Jan 29  Chinese comsat

CZ3   1984 Apr  8  Chinese comsat

CZ3   1986 Feb  1  Chinese comsat

CZ3   1988 Mar  7  Chinese comsat

CZ3   1988 Dec 22  Chinese comsat

CZ3   1990 Feb  4  Chinese comsat

CZ3   1990 Apr  7  HS-376 Asiasat 1

CZ3   1991 Dec 28  Chinese comsat

CZ3   1994 Jul 21  HS-376 Apstar 1

CZ2E  1990 Jul 16  HS-601 dummy, Test launch

CZ2E  1992 Aug 13  HS-601 Optus B1

CZ2E  1992 Dec 21  HS-601 Optus B2

CZ2E  1994 Aug 27  HS-601 Optus B3

CZ3A  1994 Feb  8  DFH-3 dummy, Test launch


 Pegasus

Jean-Jacques Serra

Orbital Science Corp. (OSC) started the design of the Air-Launched Space Booster (ASLB) alias Pegasus in April 1987. Pegasus is composed of three stages with wings, made of composit structure, powered with solif fuel and inertial guidance.

In it's standard version, Pegasus is 14.8 m long by 1.27 m diameter. It has a triangular flying surface of 6.7 m span and a rear 3-drift empennage. It weighs about 18.3 tons without the payload.

The carrier aircraft (B52 or L1011) jettisons Pegasus at 12000 m altitude at Mach 0.8. The launcher's propulsion is provided by 3 Hercules stages. The first stage is a fixed-nozzle Orion 50S, piloted by aerodynamical control surfaces. It provides 49.6 t thrust during 73 s. The second stage (same diameter) is a flexible-nozzle Orion 50 which delivers 12.5 t thurst during 72 s. The third stage is an Orion 38 with flexible nozzle that burns during 65 seconds providing 4.4 t thrust. The 2nd and 3rd stage mobile nozzles provide yawing and pitching guidance while rolling guidance is made with gas propellers which are also used for attitude control during the ballistic phases, and orientation and initial spin of the payload.

The payload mass of the standard version ranges from 270 to 410 kg depending on the orbit inclination. OSC made enhanced versions available:

- additional 4th stage (liquid fuel): HAPS (Hydrazine Auxiliary Propulsion System)

- Pegasus XL: lengthened first stage (total mass: 23.6 tons)

Since 1990 when Pegasus was first used only 9 launches occured (in 5 years). Pegasus XL launches all failed.

Pegasus launches

#	Launch id	Payload	Launch Date	Site	Type	Status/Comment (orbit in perigee x apogee x inclination x period)
1	90028	A: Pegsat B: Glomr 2 (USA 055)	5 Apr 1990	V, B52		480 km x 680 km x 94°
2	91051	Microsat 1 to 7	17 Jul 1991	V, B52	HAPS	Partial failure 350 km x 450 km x 82°
3	93009	A: Orbcomm XP 1 B: SCD	9 Feb 1993 at 14:30 UT	C, B52		730 km x 790 km x 25°
4	93026	Alexis	25 Apr 1993 at 13:56 UT	E, B52		Satellite damaged
5	94029	Step 2	19 May 1994 at 17:03 UT	V, B52	HAPS	The perigee was lower than expected 600 km x 830 km x 82°
6	n/a	Step 1	27 Jun 1994	V, L1011	XL	Failure: malfunctioned during the first stage burn, had to be destroyed
7	94046	Apex	3 Aug 1994 at 14:39 UT	V, B52		365 km x 2550 km x 70°
8	95017	A: Orbcomm FM 1 B: Orbcomm FM 2 C: Microlab 1	3 Apr 1995	V, L1011
9	n/a	Step 3	22 Jun 1995 at 19:58 UT	V, L1011	XL	Failure: interstage didn't separate from 2nd stage
10	96014	REX 2	09 Mar 1996 at 01:33 UT	V, L1011	XL

Notes: in the launch site column C stands for Cape Canaveral and released at sea, E stands for Edwards and released at Point Arguello and V stands for Vandenberg and released at Point Arguello. This indication is followed by the airplane type

Future

OSC plans to equip Pegasus XL with two turbojets. Once released at 12000 m altitude the Pegasus Turbo will be accelerated by its turbojets to reach 30000 m altitude at over Mach 4. OSC claims the 30.8 t Pegasus Turbo will be 125% more powerful than Pegasus XL and could orbit 1000 kg in LEO.


Pegasus: other future flights

SeaWifs

Forte

Minisat

24 Orbcomm FM xx

Orbview (1m imaging satellite OSC plans to launch in late 1997. Planning is already starting on OrbView 2, which will have the same resolution over a wider swath (15km instead of 4km), longer life, and a radar system to supplement its optics.)


 Proton

Jean-Jacques Serra

Gunter Krebs (listing)

The first activity of the Chelomei OKB-52 located at Reoutov near Moscow was navy missiles manufacturing. In 1959 it started producing the solid propulsion UR-96 ABM and the UR-100 (SS-11 Sego) ICBM with stockable liquid propellant. The Miassichtchev OKB-23 and the Latvotchkin OKB-301 were joined to it in 1960 and 1962 respectively.

First generation Proton

Chelomei started developping the heavy launcher UR-500 (SL-9/D) in 1961. The production started in 1962 in the Khrounitchev factory in Fili.

The first stage had a cylinder structure like the US Saturn 1: 6 UDMH tanks of about 1.8 m diameter surrounder a 4.1 m diameter NTO tank. It was powered by 6 adjustable RD-253 motors (Glouchko, NPO Energomash) of 1460 kN thrust at ground level each (SI : 317 s, 1635 kN in vacuum). The thrust of the current version of those motors (modified in 1986) is 1475 kN at ground level and 1745 kN in vacuum.

The second stage of 4.15 m diameter features a bloc of 4 RD-0210 motors (Kosberg, KB Khimautomatiki) consuming the same propellant. Each motor provided 583 kN thrust (Specific Impulsion: 327 s) during 210 seconds.

The UR-500 rocket (8K82) was 38.7 m high, weighed 562 tons and could place 12.5 tons payload on low Earth orbit. It was fired four times from Tyouratam: 2 in 1965 and 2 in 1966 and resulted in 3 successes (Proton).

Four stages Proton (SL12/D1e)

The 4-stage RU-500K was originally developped to flyby the Moon with a manned capsule. Therefore the UR-500 was equipped with 2 upper stages resulting in a 690 tons and 58 meters rocket.

The third stage (Chelomei, KB Saliout) had the same diameter as the second. It was propulsed by a single 4-vernier RD-0210 motor. Its thrust was 630 kN during 250 seconds.

The Block-D fourth stage (Korolev, NPO Energia) was derived from the Korolev's N1 lunar launcher where it was the fith stage. It consumed oxygen and kerosen with a integrated-flux motor. The latter was refirable and provided 85 kN thrust (SI = 352 s) during 600 seconds. This stage was used until 1976 before being replaced by Block-DM.

The 8K82K launcher introduced in 1967 was used for:

- lunar probes (Zond, Luna, up to 5.7 tons) and interplanetary probes (up to 4.6 tons to Mars and 5.3 tons to Venus)

- geostationary telecommunication satellites (Raduga, Ekran, Gorizont and then Luch, Gals, Express), meteorological satellite (Electro) and early warning satellite (in the Cosmos series) up to 2.4 tons.

Three stages Proton (SL13/D1)

The Proton launcher was also used in a 3-stage version to orbit payloads up to 21 tons (LEO at 200 km, 51.6° inclination)

After it's first flight in 1968 to orbit Proton 4, this version launched:

- the space stations of the manned programs (Saliout, Mir) and derived (Almaz)

- TKS type vessels (Cosmos Merkur, Kvant, Kristall, etc...)

Note: a modernized version named Proton M is announced for 1996-97. It should have new guidance systems and enhanced 2nd and 3rd stage motors. A cryogenic 4th stage is planned, so as a 5th stage derived from the Rokot Breeze.

The Proton launcher is marketed by International Launch Services (ILS)

Proton launches

#	Launch id	Payload	Launch date	Type	Status (orbit in perigee x apogee x inc. x period)
1	65054	Proton 1	16 Jul 1965
2	65087	Proton 2	2 Nov 1965
3	n/a	Proton (3a)	24 Mar 1966		F
4	66060	Proton 3	6 Jul 1966
5	67021	Cosmos 146 [L1 2]	10 Mar 1967	K Block-D	P: Stage 4 failed
6	67032	Cosmos 154 [L1 3]	8 Apr 1967	K Block-D	P: Stage 4 failed
7	n/a	Zond (4a) [L1 4]	28 Sep 1967	K Block-D	F: Stage 1 failed
8	n/a	Zond (4b) [L1 5]	21 Nov 1967	K Block-D	F: Stage 2 failed
9	68013	Zond 4 [L1 6]	2 Mar 1968	K Block-D
10	n/a	Zond (5a) [L1 7]	22 Apr 1968	K Block-D	F: Stage 2 failed at max Q
11	68076	Zond 5 [L1 9]	14 Sep 1968	K Block-D
12	68101	Zond 6 [L1 10]	10 Nov 1968	K Block-D
13	68103	Proton 4	16 Nov 1968	K
14	n/a	Zond (7a) [L1 11]	19 Jan 1969	K Block-D	F
15	n/a	Luna (15a) (Lunokhod [1])	19 Feb 1969	K Block-D	F
16	n/a	Mars (2b)	27 Mar 1969	K Block-D	F
17	n/a	Mars (2c)	2 Apr 1969	K Block-D	F
18	n/a	Luna (15b)	14 Apr 1969	K Block-D	F
19	n/a	Luna (15c)	4 Jun 1969	K Block-D	F
20	69058	Luna 15	13 Jul 1969	K Block-D
21	69067	Zond 7 [L1 12]	7 Aug 1969	K Block-D
22	68080	Cosmos 300 [Luna (16a)]	23 Sep 1969	K Block-D	P: Stage 4 failed
23	69092	Cosmos 305 [Luna (16b)]	22 Oct 1969	K Block-D	P: Stage 4 failed
24	n/a	Cosmos (311) [L1E 1, T1K #1]	16 Nov 1969	K Block-D	F
25	n/a	Cosmos (323)	6 Feb 1970	K Block-D	F
26	n/a	(?)	8 Aug 1970	K	F
27	70072	Luna 16	12 Sep 1970	K Block-D
28	70088	Zond 8 [L1 13]	20 Oct 1970	K Block-D
29	70095	Luna 17 (Lunokhod 1)	10 Nov 1970	K Block-D
30	70103	Cosmos 382 [L1E 2, T1K #2]	2 Dec 1970	K Block-D
31	71032	Salyut 1 [DOS 1]	19 Apr 1971	K
32	71042	Cosmos 419 [Mars (2d)]	10 May 1971	K Block-D	P: Stage 4 failed to ignite due to timer programming error
33	71045	Mars 2	19 May 1971	K Block-D
34	71049	Mars 3	28 May 1971	K Block-D
35	71073	Luna 18	2 Sep 1971	K Block-D
36	71082	Luna 19	28 Sep 1971	K Block-D
37	72007	Luna 20	14 Feb 1972	K Block-D
38	n/a	Salyut (2) [DOS 2]	29 Jul 1972	K	F: Stage 2 lost controll after 162 sec
39	73001	Luna 21 (Lunokhod 2)	8 Jan 1973	K Block-D
40	73017	Salyut 2 [OPS 1]	3 Apr 1973	K
41	73026	Cosmos 557 [Salyut (3), DOS 3]	11 May 1973	K
42	73047	Mars 4	21 Jul 1973	K Block-D
43	73049	Mars 5	25 Jul 1973	K Block-D
44	73052	Mars 6	5 Aug 1973	K Block-D
45	73053	Mars 7	9 Aug 1973	K Block-D
46	74017	Cosmos 0637	26 Mar 1974	K Block-DM
47	74037	Luna 22	29 May 1974	K Block-D
48	74046	Salyut 3 [OPS 2]	24 Jun 1974	K
49	74060	Molniya 1-S	29 Jul 1974	K Block-DM
50	74084	Luna 23	28 Oct 1974	K Block-D
51	74104	Salyut 4 [DOS 4]	26 Dec 1974	K
52	75050	Venera 9	8 Jun 1975	K Block-D
53	75054	Venera 10	14 Jun 1975	K Block-D
54	75097	Cosmos 0775	8 Oct 1975	K Block-DM
55	n/a	Luna (24a)	16 Oct 1975	K Block-D	F
56	75123	Raduga 01	22 Dec 1975	K Block-DM
57	76057	Salyut 5 [OPS 3]	22 Jun 1976	K
58	76081	Luna 24	9 Aug 1976	K Block-D
59	76092	Raduga 02	11 Sep 1976	K Block-DM
60	76107	Ekran 01	26 Oct 1976	K Block-DM
61	76121	Cosmos 881 Cosmos 882 [Merkur #1, #2]	15 Dec 1976	K
62	77066	Cosmos 929 [TKS Merkur #1]	17 Jun 1977	K
63	77071	Raduga 03	23 Jul 1977	K Block-DM
64	77077	Cosmos (937) Cosmos (938) [Merkur #3, #4]	4 Aug 1977	K	F
65	77092	Ekran 02	20 Sep 1977	K Block-DM
66	77097	Salyut 6 [DOS 5]	29 Sep 1977	K
67	78032	Cosmos 997 Cosmos 998 [Merkur #5, #6]	30 Mar 1978	K
68	n/a	Ekran (3a)	27 May 1978	K Block-DM	F
69	78073	Raduga 04	18 Jul 1978	K Block-DM
70	n/a	Ekran (3b)	17 Aug 1978	K Block-DM	F
71	78084	Venera 11	9 Sep 1978	K Block-DM
72	78086	Venera 12	14 Sep 1978	K Block-DM
73	n/a	Ekran (3c)	17 Oct 1978	K Block-DM	F
74	78118	Gorizont 01	19 Dec 1978	K Block-DM	P: Stage 4 failed to reignite
75	n/a	Cosmos (1070) / Cosmos (1071) [Merkur #7, #8]	5 Jan 1979	K	F
76	79015	Ekran 03	21 Feb 1979	K Block-DM
77	79035	Raduga 05	25 Apr 1979	K Block-DM
78	79042	Cosmos 1100 / Cosmos 1101 [Merkur #9, #10]	22 May 1979	K
79	79062	Gorizont 02	5 Jul 1979	K Block-DM
80	79087	Ekran 04	3 Oct 1979	K Block-DM
81	79105	Gorizont 03	28 Dec 1979	K Block-DM
82	80016	Raduga 06	20 Feb 1980	K Block-DM
83	80049	Gorizont 04	14 Jun 1980	K Block-DM
84	80060	Ekran 05	15 Jul 1980	K Block-DM
85	80081	Raduga 07	5 Oct 1980	K Block-DM
86	80104	Ekran 06	26 Dec 1980	K Block-DM
87	81027	Raduga 08	18 Mar 1981	K Block-DM
88	81039	Cosmos 1267	25 Apr 1981	K
89	81061	Ekran 07	26 Jun 1981	K Block-DM
90	81069	Raduga 09	30 Jul 1981	K Block-DM
91	81102	Raduga 10	9 Oct 1981	K Block-DM
92	81106	Venera 13	30 Oct 1981	K Block-DM
93	81110	Venera 14	4 Nov 1981	K Block-DM
94	82009	Ekran 08	5 Feb 1982	K Block-DM
95	82020	Gorizont 05	15 Mar 1982	K Block-DM
96	82033	Salyut 7 [DOS 6]	19 Apr 1982	K
97	82044	Cosmos 1366	17 May 1982	K Block-DM
98	n/a	Ekran (9a)	23 Jul 1982	K Block-DM	F
99	82093	Ekran 09	16 Sep 1982	K Block-DM
100	82100	Cosmos 1414 [Uragan #1]/Cosmos 1413,1415[Dummy]	12 Oct 1982	K Block-DM2
101	82103	Gorizont 06	20 Oct 1982	K Block-DM2
102	82113	Raduga 11	26 Nov 1982	K Block-DM2
103	n/a	Raduga (12a)	24 Dec 1982	K Block-DM2	F
104	83013	Cosmos 1443	2 Mar 1983	K
105	83016	Ekran 10	12 Mar 1983	K Block-DM2
106	83020	Astron	23 Mar 1983	K Block-DM2
107	83028	Raduga 12	8 Apr 1983	K Block-DM2
108	83053	Venera 15	2 Jun 1983	K Block-DM2
109	83054	Venera 16	7 Jun 1983	K Block-DM2
110	83066	Gorizont 07	1 Jul 1983	K Block-DM2
111	83084	Cosmos 1490-1491 [Uragan #2,3]/Cosmos 1492[Dummy]	10 Aug 1983	K Block-DM2
112	83088	Raduga 13	25 Aug 1983	K Block-DM2
113	83100	Ekran 11	29 Sep 1983	K Block-DM2
114	83118	Gorizont 08	30 Nov 1983	K Block-DM2
115	83127	Cosmos 1519-1520 [Uragan #4,5]/Cosmos 1521[Dummy]	29 Dec 1983	K Block-DM2
116	84016	Raduga 14	15 Feb 1984	K Block-DM2
117	84022	Cosmos 1540	2 Mar 1984	K Block-DM2
118	84028	Ekran 12	16 Mar 1984	K Block-DM2
119	84031	Cosmos 1546	29 Mar 1984	K Block-DM2
120	84041	Gorizont 09	22 Apr 1984	K Block-DM2
121	84047	Cosmos 1554-1555 [Uragan #6,7]/Cosmos 1556[Dummy]	19 May 1984	K Block-DM2
122	84063	Raduga 15	22 Jun 1984	K Block-DM2
123	84078	Gorizont 10	1 Aug 1984	K Block-DM2
124	84090	Ekran 13	24 Aug 1984	K Block-DM2
125	84095	Cosmos 1593,1595 [Uragan #8,9]/Cosmos 1594[Dummy]	4 Sep 1984	K Block-DM2
126	84106	Cosmos 1603 [Tselina-2  #1]	28 Sep 1984	K Block-DM2
127	84125	Vega 1	15 Dec 1984	K Block-DM2
128	84128	Vega 2	21 Dec 1984	K Block-DM2
129	85007	Gorizont 11	18 Jan 1985	K Block-DM2
130	85016	Cosmos 1629	21 Feb 1985	K Block-DM2
131	85024	Ekran 14	22 Mar 1985	K Block-DM2
132	85037	Cosmos 1650-1651 [Uragan #10-11]/Cosmos-1652[Dummy]	17 May 1985	K Block-DM2
133	85042	Cosmos 1656 [Tselina-2 #2]	30 May 1985	K Block-DM2
134	85070	Raduga 16	8 Aug 1985	K Block-DM2
135	85086	Cosmos 1686 [TKS Merkur #4]	27 Sep 1985	K
136	85102	Cosmos 1700 [Luch #1, Altair #1]	25 Oct 1985	K Block-DM2
137	85107	Raduga 17	15 Nov 1985	K Block-DM2
138	85118	Cosmos 1710-1711 [Uragan #12-13]/Cosmos-1712[Dummy]	24 Dec 1985	K Block-DM2
139	86007	Raduga 18	17 Jan 1986	K Block-DM2
140	86017	Mir 1 [DOS 7]	19 Feb 1986	K
141	86027	Cosmos 1738	4 Apr 1986	K Block-DM2
142	86038	Ekran 15	24 May 1986	K Block-DM2
143	86044	Gorizont 12	10 Jun 1986	K Block-DM2
144	86071	Cosmos 1778-1780 [Uragan #14-16]	16 Sep 1986	K Block-DM2
145	86082	Raduga 19	25 Oct 1986	K Block-DM2
146	86090	Gorizont 13	18 Nov 1986	K Block-DM2
147	87002	Cosmos [1811] [Almaz-T #1]	29 Dec 1986	K	F
148	87010	Cosmos 1817 <Geosynch Failure>	30 Jan 1987	K Block-DM2	P: Stage 4 failed
149	87028	Raduga 20	19 Mar 1987	K Block-DM2
150	87030	Kvant 1	31 Mar 1987	K
151	87036	Cosmos 1838-1840 [Uragan #17-19]	24 Apr 1987	K Block-DM2	P: Stage 4 failed to reignite
152	87040	Gorizont 14	11 May 1987	K Block-DM2
153	87064	Cosmos 1870	25 Jul 1987	K
154	87073	Ekran 16	3 Sep 1987	K Block-DM2
155	87079	Cosmos 1883-1885 [Uragan #20-22]	16 Sep 1987	K Block-DM2
156	87084	Cosmos 1888	1 Oct 1987	K Block-DM2
157	87091	Cosmos 1894	28 Oct 1987	K Block-DM2
158	87096	Cosmos 1897	26 Nov 1987	K Block-DM2
159	87100	Raduga 21	10 Dec 1987	K Block-DM2
160	87109	Ekran 17	27 Dec 1987	K Block-DM2
161	n/a	Gorizont [15]	18 Jan 1988	K Block-DM2	F: Stage 3 failed
162	88009	Cosmos 1917-1919 [Uragan #23-25]	17 Feb 1988	K Block-DM2	P: Stage 4 failed
163	88028	Gorizont 15	31 Mar 1988	K Block-DM2
164	88034	Cosmos 1940 [Prognoz #1]	26 Apr 1988	K Block-DM2
165	88036	Ekran 18	6 May 1988	K Block-DM2
166	88043	Cosmos 1946-1948 [Uragan #26-28]	21 May 1988	K Block-DM2
167	88058	Fobos 1	7 Jul 1988	K Block-DM2
168	88059	Fobos 2	12 Jul 1988	K Block-DM2
169	88066	Cosmos 1961	1 Aug 1988	K Block-DM2
170	88071	Gorizont 16	18 Aug 1988	K Block-DM2
171	88085	Cosmos 1970 Cosmos 1971 Cosmos 1972	16 Sep 1988	K Block-DM2
172	88095	Raduga 22	20 Oct 1988	K Block-DM2
173	88108	Ekran 19	10 Dec 1988	K Block-DM2
174	89001	Cosmos 1987 Cosmos 1988 Cosmos 1989	10 Jan 1989	K Block-DM2
175	89004	Gorizont 17	26 Jan 1989	K Block-DM2
176	89030	Raduga 23	14 Apr 1989	K Block-DM2
177	89039	Cosmos 2022 Cosmos 2023 Cosmos 2024	31 May 1989	K Block-DM2
178	89048	Raduga 1-1	21 Jun 1989	K Block-DM2
179	89052	Gorizont 18	5 Jul 1989	K Block-DM2
180	89081	Gorizont 19	28 Sep 1989	K Block-DM2
181	89093	Kvant 2	26 Nov 1989	K
182	89096	Granat	1 Dec 1989	K Block-DM2
183	89098	Raduga 24	15 Dec 1989	K Block-DM2
184	89101	Cosmos 2054	27 Dec 1989	K Block-DM2
185	90016	Raduga 25	15 Feb 1990	K Block-DM2
186	90045	Cosmos 2079 Cosmos 2080 Cosmos 2081	19 May 1990	K Block-DM2
187	90048	Kristall	31 May 1990	K
188	90054	Gorizont 20	20 Jun 1990	K Block-DM2
189	90061	Cosmos 2085	18 Jul 1990	K Block-DM2
190		?	9 Aug 1990	K Block-DM2	F: Stage 2 failed due to forgotten rag in a fuel line
191	90094	Gorizont 21	3 Nov 1990	K Block-DM2
192	90102	Gorizont 22	23 Nov 1990	K Block-DM2
193	90110	Cosmos 2109 Cosmos 2110 Cosmos 2111	8 Dec 1990	K Block-DM2
194	90112	Raduga 26	20 Dec 1990	K Block-DM2
195	90116	Raduga 1-2	27 Dec 1990	K Block-DM2
196	91010	Cosmos 2133	14 Feb 1991	K Block-DM2
197	91014	Raduga 27	28 Feb 1991	K Block-DM2
198	91024	Almaz 1 [Almaz-T #3]	31 Mar 1991	K
199	91025	Cosmos 2139 Cosmos 2140 Cosmos 2141	4 Apr 1991	K Block-DM2
200	91046	Gorizont 23	2 Jul 1991	K Block-DM2
201	91064	Cosmos 2155	13 Sep 1991	K Block-DM2
202	91074	Gorizont 24	23 Oct 1991	K Block-DM2
203	91079	Cosmos 2172	22 Nov 1991	K Block-DM2
204	91087	Raduga 28	19 Dec 1991	K Block-DM2
205	92005	Cosmos 2177 Cosmos 2178 Cosmos 2179	29 Jan 1992	K Block-DM2
206	92017	Gorizont 25	2 Apr 1992	K Block-DM2
207	92043	Gorizont 26	14 Jul 1992	K Block-DM2
208	92047	Cosmos 2204 Cosmos 2205 Cosmos 2206	29 Jul 1992	K Block-DM2
209	92059	Cosmos 2209	10 Sep 1992	K Block-DM2
210	92074	Ekran 20	30 Oct 1992	K Block-DM2
211	92082	Gorizont 27	27 Nov 1992	K Block-DM2
212	92088	Cosmos 2224	17 Dec 1992	K Block-DM2
213	93010	Cosmos 2234 Cosmos 2235 Cosmos 2236	17 Feb 1993	K Block-DM2
214	93013	Raduga 29	25 Mar 1993	K Block-DM2
215	n/a	Gorizont #39	27 May 1993	K Block-DM2	F: Stage 2 failed because contaminated UDMH destroyed an engine
216	93062	Raduga 30	30 Sep 1993	K Block-DM2
217	93069	Gorizont 28	28 Oct 1993	K Block-DM2
218	93072	Gorizont 29	18 Nov 1993	K Block-DM2
219	94002	Gals 1	20 Jan 1994	K Block-DM2M
220	94008	Raduga 1-3	5 Feb 1994	K Block-DM2
221	94012	Raduga 31	18 Feb 1994	K Block-DM2
222	94021	Cosmos 2275 Cosmos 2276 Cosmos 2277	11 Apr 1994	K Block-DM2
223	94030	Gorizont 30	20 May 1994	K Block-DM2
224	94038	Cosmos 2282	6 Jul 1994	K Block-DM2
225	94050	Cosmos 2287 Cosmos 2288 Cosmos 2289	11 Aug 1994	K Block-DM2
226	94060	Cosmos 2291	21 Sep 1994	K Block-DM2
227	94067	Express 1	13 Oct 1994	K Block-DM2M
228	94069	Electro 1	31 Oct 1994	K Block-DM2M
229	94076	Cosmos 2294 Cosmos 2295 Cosmos 2296	20 Nov 1994	K Block-DM2
230	94082	Luch 0	16 Dec 1994	K Block-DM2
231	94087	Raduga 32	28 Dec 1994	K Block-DM2
232	95009	Cosmos 2307 Cosmos 2308 Cosmos 2309	7 Mar 1995	K Block-DM2
233	95024	Spektr	20 May 1995	K
234	95037	Cosmos 2316 Cosmos 2317 Cosmos 2318	24 Jul 1995	K Block-DM2
235	95045	Cosmos 2319	30 Aug 1995	K Block-DM2
236	95054	Luch 1	11 Oct 1995	K Block-DM2M
237	95063	Gals 2	17 Nov 1995	K Block-DM2
238	95068	Cosmos 2323 Cosmos 2324 Cosmos 2325	14 Dec 1995	?
239	96005	Gorizont 31	25 Jan 1996	?
240	96010	Raduga 33	19 Feb 1996	K Block-DM2

Notes: All launches from Tyouratam.


 Rokot

Jean-Jacques Serra

The primary activity of Chelomei's OKB-52 was navy missiles production. In 1959 the firm started producing more important missiles such as the solid propulsion UR-96 ABM and the UR-100 (SS-11 Sego) ICBM with stockable liquid propellant. 1030 copies of this light ICBM (50 tons) of 3rd generation were deployed in the 60ies and 70ies.

Origin: Inter Continental Ballistic Missile (ICBM) of fourth generation

After designing the RU-200 ICBM and the UR-500 Proton space launcher Chelomei's OKB (now NPO Saliout) developped a new ICBM know as UR-100N or RS-18 (or SS-19 Stilleto) between 1964 and 1975. 360 copies of the 4th generation ICBM were manufactured in the 70ies and 80ies.

Few characteristics on this missile are known apart that it has 2 stages with stockable liquid propellant. The first stage motor has 4 combustion chambers. The second stage motor is built by NPO Klimov. Its mass at launch time is about 90 tons; its height is 27 meters and width is 2.5 meters.

The rokot launcher

The launcher is a SS-19 missile to which a Breeze 3rd stage has been added (or Briz?). Breeze weighs 6.4 tons and is 3.4 m long for 2.2 m diameter. Its in-flight refirable motor uses stockable propellant (NTO-UDMH). The launcher can orbit 1 to 2 tons of payload in LEO.

Two suborbital tests of Rokot were carried out on 20 Nov 1990 and 20 Dec 1991 before launching its first satellite.

It should be marketed by Eurockot Launch Services GmbH (Khrunichev and DASA) in 1997. A launch should cost from 7 to 10 million dollars. The first launches should take place in Plesetk before being transfered at Svobodny in the Russian far East.

Rokot launches

#	Launch id	Payload	Launch date	Status (orbit in perigee x apogee x inc. x period)
1	94085	RS 15	26 Dec 1994 at 03:00 UT	The spent third stage exploded a few hours after launch

Notes: All launches from Plesetsk.


 Scout

Jean-Jacques Serra

Gunter Krebs (listing)

The Scout rocket was designed in 1957 by the NACA Langley center (which becamed the NASA Langley Research Center). It was mass produced from 1959 on by Vought Corp. (to become LTV). Scout was 21 m high, weighed 16 tons and was solid fuel only. It was used as light launcher so as sounding rocket. The first stage was an Algol made by Aerojet of 1.1 m diameter which provided 52 t thrust. Algol was controlled by a jet deflector called jetavator which has been designed for the Polaris program. The second stage was a Thiokol Castor derived from the tactical Sergeant missile and provided 24 t thrust. The two upper stages were built by Alleghany Ballistics (now Hercules). The third stage was a 6.2 t thrust Antares and the fourth stage a 1.4 t Altair.

The first launches of Scout in 1960 were ballistic flights. The first orbiting attempt failed in December 1960, but on 16 February 1961 Scout successfuly delivered Explorer 09 in orbit. Since then all its stages have been improved. One USAF specific version was called Blue Scout and a Blue Scout Junior (3-stage, Algol-less) was fired 22 times on ballistic missions.

Scouts were fired from 3 locations: Wallops Island, Vandenberg and San Marco. The latter is an italian oil platform at large from Kenya which only fired Scouts. Production of the Scout stopped in 1982 but the last vehicle was fired in 1994. This latter version (Scout G1) was 23 m high and weighed 21.7 tons.

Evolution of Scout [chart 1]

Designation	First launch	1st stage	2nd stage	3rd stage	4th stage	inc: 90° (1)	inc: 38° (1)	inc: 2.9° (1)
Scout X-1	1960	Algol 1C	Castor 1	Antares 1	Altair 1	45	59
Scout X-2	1962	Algol 1D	Castor 1	Antares 2	Altair 1	59	76
Scout X-3	1963	Algol 2A	Castor 1	Antares 2	Altair 1	68	87
Scout X-4	1964	Algol 2B	Castor 1	Antares 2	Altair 2	80	103
Scout A-1	1965	Algol 2B	Castor 2	Antares 2	Altair 2	94	122
Scout B-1	1965	Algol 2B	Castor 2A	Antares 2A	Altair 3A	116	143	151
Scout D-1	1972	Algol 3A	Castor 2A	Antares 2A	Altair 3A	148	185	198
Scout F-1	1974	Algol 3A	Castor 2A	Antares 2B	Altair 3A	156	193	203
Scout G-1	1974	Algol 3A	Castor 2A	Antares 3A	Altair 3A	166	208	220

Notes: (1) Payload (kg) in circular 550 km orbit; Launches from Vandenberg (90°), Wallops Island (38°) and San Marco (2.9°)

Scout was used both by NASA and USAF (see chart 2). It was used for:

- Scientific satellites of America (Explorer program), international organizations (ESRO) and other countries (Ariel, San Marco, FR 1, Eole, Azur, Aeros, Miranda, ANS)

- US satellites for military, navigation (Transit, Triad, Nova, etc.) and technology (OV3, MSTI, etc.) purposes

Scout launches [chart 2]

#	Launch id	Payload	Launch Date	Site	Type	Status/Comment (orbit in perigee x apogee x inclination x period)
1, ST-1	n/a	NASA radiation probe	02 Sep 1960	W	X1	Ballistic flight
2, ST-2	n/a	USAF radiation probe	4 Oct 1960	W	X1	Failure Ballistic flight
3, ST-3	n/a	Explorer S56	04 Dec 1960	W	X1	Failure
4, ST-4	61004	Explorer 09	16 Feb 1961	W	X1	634x2583x38.9
5, ST-5	n/a	Explorer S55	30 Jun 1961	W	X1	Failure
6, ST-6	61022	Explorer 13	25 Aug 1961	W	X1	Partial failure
7, ST-7	n/a	P 21	19 Oct 1961	W	X1	Failure Ballistic flight
8, ST-8	n/a	Reentry 1	1 Mar 1962	W	X1A	Ballistic flight
9, ST-9	n/a	P 21A	29 Mar 1962	W	X2	Ballistic flight
10, 111	n/a	Solrad 4B	26 Apr 1962	V	X2	Failure
11, 112	n/a	P35 1	24 May 1962	V	X2M	Failure
12, 117	62039	P35 2 (FTV 3502)	23 Aug 1962	V	X2M	650x858x98.6
13, 114	n/a	Reentry 2	31 Aug 1962	W	X3A	Failure
14, 115	62070	Explorer 16	16 Dec 1962	W	X3
15, 118	62071	Transit 5A-1	19 Dec 1962	V	X3	698x725x90.6
16, 126	63005	P35 3 (FTV 0240)	19 Feb 1963	V	X3M	505x791x100.5
17, 119	n/a	Transit 5A-2	05 Apr 1963	V	X3	Failure
18, 121	n/a	P35 4	26 Apr 1963	V	X2M	Failure
19, 116	n/a	RFD 1	22 May 1963	W	X3	Ballistic flight
20, 120	63022	Transit 5A-3	16 Jun 1963	V	X3	727x757x90.0
21, 113	63026	GRS (CRL 1)	28 Jun 1963	W	X4	411x1311x69.7
22, 110	n/a	Reentry 3	27 Jul 1963	W	X3M	Failure Ballistic flight
23, 132	n/a	P35 5	27 Sep 1963	V	X2B	Failure
24, 122R	63053	Explorer 19	19 Dec 1963	V	X4
25, 127R	64015	Ariel 2	27 Mar 1964	W	X3
26, 125R	64026	Transit 5C-1	04 Jun 1964	V	X4	854x956x90.4
27, 128R	n/a	ESRS (CRL 2)	25 Jun 1964	V	X4	Failure
28, 124R	n/a	SERT 1	20 Jul 1964	W	X4	Ballistic flight
29, 129R	n/a	Reentry 4A	18 Aug 1964	W	X4A	Ballistic flight
30, 134R	64051	Explorer 20	25 Aug 1964	V	X4
31, 130R	n/a	RFD 2	9 Oct 1964	W	X3C	Ballistic flight
32, 123R	64064	Explorer 22	10 Oct 1964	V	X4
33, 133R	64074	Explorer 23	06 Nov 1964	W	X4
34, 135R	64076	A: Explorer 24 B: Explorer 25	21 Nov 1964	V	X4
35, 137R	64084	San Marco 1	15 Dec 1964	W	X4
36, 136R	65032	Explorer 27	29 Apr 1965	W	X4
37, 131R	65063	Secor 05	10 Aug 1965	W	B
38, 138R	65093	Explorer 30	19 Nov 1965	W	X4
39, 139R	65101	FR 1	06 Dec 1965	V	X4
40, 140C	65109	Transit-O 6	22 Dec 1965	V	A	909x1086x89.1
41, 142C	66005	Transit-O 7	28 Jan 1966	V	A	861x1217x89.7
42, 141C	n/a	Reentry 4B	9 Feb 1966	W	X4A	Ballistic flight
43, 143C	66024	Transit-O 8	26 Mar 1966	V	A	891x1128x89.7
44, 145C	66034	OV 3-1	22 Apr 1966	V	B
45, 146C	66041	Transit-O 9	19 May 1966	V	A	863x980x90.0
46, 147C	66052	OV 3-4	10 Jun 1966	W	B
47, 148C	66070	OV 3-3	04 Aug 1966	V	B
48, 149C	66076	Transit-O 10	18 Aug 1966	V	A	1056x1101x88.9
49, 150C	66097	OV 3-2	28 Oct 1966	V	B
50, 151C	n/a	OV3-5	31 Jan 1967	V	B	Failure
51, 154C	67034	Transit-O 12	14 Apr 1967	V	A	1053x1083x90.2
52, 153C	67038	San Marco 2	26 Apr 1967	S	B
53, 155C	67042	Ariel 3	05 May 1967	V	A
54, 156C	67048	Transit-O 13	18 May 1967	V	A	1074x1116x89.3
55, 156C	n/a	Esro 2A (Iris 1)	29 May 1967	V	B	Failure
56, 157C	67092	Transit-O 14	25 Sep 1967	V	A	1041x1116x89.3
57, 159C	n/a	RAM C1	19 Oct 1967	W	B	Ballistic flight
58, 158C	67120	OV 3-6 (Atcos 2)	05 Dec 1967	V	B	412x439x90.7
59, 162C	68012	Transit-O 18	02 Mar 1968	V	A	1035x1139x90.0
60, 160C	68017	Solrad 09	05 Mar 1968	W	B	Partial failure
61, 160C	n/a	Reentry 5	27 Apr 1968	W	X5A	Ballistic flight
62, 164C	68041	Esro 2B	17 may 1968	V
63, 165C	68066	A: Explorer 39 B: Explorer 40	08 Aug 1968	V	B
64, 168C	n/a	RAM C2	22 Aug 1968	W	B	Ballistic flight
65, 167C	68084	Esro 1A	03 Oct 1968	V	B
66, 172C	69083	Esro 1B	01 Oct 1969	V	B
67, 169C	69097	Azur	08 Nov 1969	V	B
68, 176C	70067	Transit-O 19	27 Aug 1970	V	A	954x1221x90.2
69, 171C	n/a	RAM C3	30 Sep 1970	W	B	Ballistic flight
70, 174C	70094	A: OFO B: RM 1	09 Nov 1970	W	B
71, 175C	70107	Explorer 42	12 Dec 1970	S	B
72, 173C	71036	San Marco 3	24 Apr 1971	S	B
73, 144CR	n/a	PAET	20 Jun 1971	W	B	Ballistic flight
74, 177C	71058	Solrad 10	08 Jul 1971	W	B
75, 180C	71071	Eole	16 Aug 1971	W	B1
76, 166CR	n/a	GRP	20 Sep 1971	W	B	Ballistic flight
77, 163CR	71096	Explorer 45	15 Nov 1971	S	B
78, 183C	71109	Ariel 4	11 Dec 1971	V	B1
79, 184C	72061	Explorer 46	13 Aug 1972	W	D1
80, 182C	72069	Triad 1 (TIP 1)	02 Sep 1972	V	B1	716x863x90.1
81, 170CR	72091	Explorer 48	15 Nov 1972	S	D1
82, 185C	72092	Esro 4	22 Nov 1972	V	D1
83, 181C	72100	Aeros 1	16 Dec 1972	V	D1
84, 178C	73081	Transit-O 20	30 Oct 1973	V	A1	907x1136x90.2
85, 190C	74009	San Marco 4	18 Feb 1974	S	D1
86, 188C	74013	Miranda	09 Mar 1974	V	D1
87, 191C	74040	Explorer 52	03 Jun 1974	V	E1
88, 186C	74055	Aeros 2	16 Jul 1974	V	D1
89, 189C	74070	ANS	30 Aug 1974	V	D1
90, 187C	74077	Ariel 5	15 Oct 1974	S	B1
91, 194	75037	Explorer 53	07 May 1975	S	F1
92, 195C	75099	Triad 2 (TIP 2)	12 Oct 1975	V	D1	362x705x90.7
93, 196C	n/a	Explorer [56] Explorer [57]	05 Dec 1975	V	F1	Failure
94, 179CR	76047	Wideband (P76 5)	22 May 1976	V	B1	995x1059x99.6
95, 193C	n/a	Gravity probe	18 Jun 1976	W	D1	Ballistic flight
96, 197C	76089	Triad 3 (TIP 3)	01 Sep 1976	V	D1	475x930x89.9
97, 200C	77106	Transat (O 11)	28 Oct 1977	V	D1	1000x1000x89.9
98, 201C	78041	AEM 1	26 Apr 1978	V	D1
99, 202C	79013	AEM 2	18 Feb 1979	W	D1
100, 198C	79047	Ariel 6	02 Jun 1979	W	D1
101, 203C	79094	AEM 3	30 Oct 1979	V	G1
102, 192C	81044	Nova 1	15 May 1981	V	G1
103, 205C	83063	Hilat (T83 1)	27 Jun 1983	V	G1	770x838x82.0
104, 208C	84110	Nova 2	12 Oct 1984	V	G1
105, 209C	85066	Transit-O 24 Transit-O 30	03 Aug 1985	V	G1	1000x1260x89.8
106, 207C	85114	ITV 1/2	13 Dec 1985	W	G1	316x770x37.0
107, 199C	86088	Polar Bear (P87 1)	14 Nov 1986	V	G1	1170x1180x90.0
108, 204C	87080	Transit-O 27 Transit-O 29	16 Sep 1987	V	G1	1020x1180x90.0
109, 209C	88026	San Marco 5	25 Mar 1988	S	G1
110, 211C	88033	Transit-O 23 Transit-O 32	25 Apr 1988	V	G1	1020x1300x90.0
111, 213C	88052	Nova 3	16 Jun 1988	V	G1
112, 214C	88074	Transit-O 25 Transit-O 31	25 Aug 1988	V	G1	1030x1180x90.0
113, 212C	90043	Macsat 1 Macsat 2	09 May 1990	V	G1	610x770x90.0
114, 216C	91045	REX 1	29 Jun 1991	V	G1	770x870x89.6
115, 215C	92038	Sampex (SMEX 1)	03 Jul 1992	V	G1	510x690x81.7
116, 210C	92078	MSTI 1	21 Nov 1992	V	G1
117, 217C	93041	Radcal	25 Jun 1993	V	G1
118, 218C	94028	MSTI 2	09 May 1994	V	G1

Notes: Launch site: C for Cape Canaveral, V for Vandenberg, W for Wallops Island and S for San Marco

[Gunter Krebs adds:]

Although mostly neglected and not part of the "official" launch history, the Blue-Scout-1 and Blue Scout-2 versions will be included in next version of TSE. The main difference was, that the Blue-Scouts had an different aft section of the first stage as they stood on the launch pad (the "normal" Scout was

suspended on a launch tower). The Blue-Scout-1 was a 3 stage version of the Scout-X1, the Blue Scout-2 was mostly identical to the Scout-X1.

The Blue-Scout-2 made one illfated attempt to launch a satellite from Cape Canaveral:

01.11.1961 Mercury-MS 1

The Mercury-MS 1 payload was a small communication satellite to simmulate the telemetry from a manned Mercury capsule. No replacement was launched.


 Start

Jean-Jacques Serra

The development of powder ballistic missiles started in 1958 in Russia. It was carried out by a division created by Korolev (today NPO Soyouz) directed by I. Sadovsky and after 1966 by A.D. Nadiradze. The first ICBM was the 3-stage RS-12 (SS-13 Savage) with metallic structure. Only 60 items were produced. Two mobile missiles were then derived from it: the SS-14 which used the 2 upper stages of the SS-13 and the SS-15 which refurbished the first and third stage.

In the seventies the RS-14 ICBM (SS-16 Sinner) was a much improved version of the RS-12, especially for the reeled structure and the guidance. This ICBM was not deployed following the SALT agreements. The RSD-10 IRBM (SS-20 Sabre) produced to replace the aging SS-4 and SS-5 were deployed (up to 378 operational) before being retrieved with the INF agreements.

Origin: Inter Continental Ballistic Missile (ICBM) of fith generation

At the beginning of the eighties the NPO Soyouz designed a new mobile ICBM named RS-12M Topol (SS-25 Sickle) to replace old launching silos. This fith generation missile which was operational in 1985 is the biggest mobile strategic missile of the CIS. According to the Russians the SS-25 is derived from the SS-13. With 3 stages it is 18.5 m long, 1.8 m diameter and weighs about 40 tons. It can send a 1 ton payload to more than 10000 km.

The Start launcher

The first version Start 1 is a 4-stage launcher which 3 first stages are derived from the SS-25. it is 22.7 m high, weighs 47 tons at takeoff and can deliver 300 kg on polar orbit ot 500 kg in equatorial orbit. It was tested only once in March 1993.

The Start offered for commercial flights has an additional stage: an improved version of SS-20's second stage is inserted between the first and second stage. The whole is then 29 m high and 60 tons. It can put 450 kg in polar orbit. It's first launch in March 1995 failed.

Start launches

#	Launch id	Payload	Launch date	Type	Status (orbit in perigee x apogee x inc. x period)
1	93014	Start 1	25 Mar 1993	4-stage
2	FTO	Gurwin 1 Unamsat 1	28 Mar 1995	5-stage	Failure cause: 5th stage failed


 STS

Space Transport System

American space Shutle program

The orbiter is 45 m long, 14.4 m wide and weights 67.5 t. It can carry 8 persons and a 29 t bay. It is launched with a 700 t tank.


STS

[launch vehicle index]

STS 01 STS 02 STS 03 STS 04 STS 05 STS 06 STS 07 STS 08 STS 09 STS 11 STS 13 STS 16 STS 17 STS 19 STS 20 STS 23 STS 24 STS 25 STS 26 STS 26R	STS 27 STS 27R STS 28 STS 28R STS 29 STS 30 STS 30R STS 31 STS 31R STS 32 STS 32R STS 33 STS 33R STS 34 STS 35 STS 36 STS 37 STS 38 STS 39 STS 40	STS 41 STS 42 STS 43 STS 44 STS 45 STS 46 STS 47 STS 48 STS 49 STS 50 STS 51 STS 52 STS 53 STS 54 STS 55 STS 56 STS 57 STS 58 STS 59 STS 60	STS 61 STS 62 STS 63 STS 64 STS 65 STS 66 STS 67 STS 68 STS 69 STS 70 STS 71 STS 72 STS 73 STS 74 STS 75 STS 76


 STS 01

General

Launch id	81034
Launch date	12 Apr 1981
Launch site	Cape Canaveral pad 39A
Type	Columbia #01
Crew	John Young Robert Crippen
Landing date	14 Apr 1981
Landing site	Edwards
Payload	none

Flight of 54 h 20 min 52 s

DFI mission


 STS 02

General

Launch id	81111
Launch date	12 Nov 1981
Launch site	Cape Canaveral pad 39A
Type	Columbia #02
Crew	Richard Truly Joseph Engle
Landing date	14 Nov 1981
Landing site	Edwards
Payload	none

Flight of 54 h 13 min 12 s. The flight was shorten

OSTA 1 mission: 7 experiences


 STS 03

General

Launch id	82022
Launch date	22 Mar 1982
Launch site	Cape Canaveral pad 39A
Type	Columbia #03
Crew	Jack Lousma Charles Fullerton
Landing date	30 Mar 1982
Landing site	White Sands
Payload	none

Flight of 8 days 5 min

OSS 1 mission


 STS 04

General

Launch id	82065
Launch date	27 Jun 1982
Launch site	Cape Canaveral pad 39A
Type	Columbia #04
Crew	Thomas Mattingly Henry Harstfield
Landing date	4 Jul 1982
Landing site	Edwards
Payload	none

Flight of 7 days 1 h 9 min 39 s

DoD 82-1 mission


 STS 05

General

Launch id	82110
Launch date	11 Nov 1982
Launch site	Cape Canaveral
Type	Columbia #05
Crew	Vance Brand Robert Overmyer Joseph Allen William Lenoir
Landing date	16 Nov 1982
Landing site	Edwards
Payload	B: SBS 3 C: Anik C3

First operational flight: 5 days 2 h 14 min 25 s


 STS 06

General

Launch id	83026
Launch date	4 Apr 1983
Launch site	Cape Canaveral
Type	Challenger #01
Crew	Donald Peterson Story Musgrave Paul Weitz Karol Bobko
Landing date	9 Apr 1983
Landing site	Edwards
Payload	B: TDRS 1

Flight of 5 days 24 min 32 s

Musgrave and Peterson worked 3 h 50 min in space to simulate repairings


 STS 07

General

Launch id	83059
Launch date	18 Jun 1983
Launch site	Cape Canaveral
Type	Challenger #02
Crew	Robert Crippen Frederik Hauck Sally Ride (first american woman in space) Normand Thagard John Fabian
Landing date	24 Jun 1983
Landing site	Edwards
Payload	B: Anik C2 C: Palapa B1 D: Spas 1 (launched and retrieved)

Flight of 6 days 2 h 24 min 10 s


 STS 08

General

Launch id	83089
Launch date	30 Aug 1983
Launch site	Cape Canaveral
Type	Challenger #03
Crew	Richard Truly Daniel Brandenstein Dale Gardner Gruion Bluford William Thornton
Landing date	5 Sep 1983
Landing site	Edwards
Payload	B: Insat 1B

Flight of 6 days 1 h 8 min 40 s


 STS 09

Also called STS 41A

General

Launch id	83116
Launch date	28 Nov 1983
Launch site	Cape Canaveral pad 39A
Type	Columbia #06
Crew	John Young Brewster Shaw Owen Garriott Robert Parker Byron Lichtenberg Ulf Merbold (Germany)
Landing date	8 Dec 1983
Landing site	Edwards
Payload	none

Flight of 10 days 7 h 47 min

Spacelab 1 mission (70 experiences)


 STS 11

Also called STS 41B

General

Launch id	84011
Launch date	3 Feb 1984
Launch site	Cape Canaveral
Type	Challenger #04
Crew	Vance Brand Robert Gibson Ronald Mc Nair Bruce Mc Candless Robert Stewart
Landing date	11 Feb 1984
Landing site	Cape Canaveral
Payload	B: Westar 6 C: IRT (launched and retrieved) D: Palapa B2

Flight of 7 days 23 h 17 min

First free flight for Mc Candless and Stewart with the Manned Manoeuvring Unit (MMU)


 STS 13

Also called STS 41C

General

Launch id	84034
Launch date	6 Apr 1984
Launch site	Cape Canaveral
Type	Challenger #05
Crew	Robert Crippen Francis Scobee Terry Hart George Nelson James Van Hoften
Landing date	13 Apr 1984
Landing site	Edwards
Payload	LDEF

Flight of 6 days 23 h 40 min

Reparation of SMM in orbit by Nelson and Van Hoften


 STS 16

Also called STS 41D

General

Launch id	84093
Launch date	30 Aug 1984
Launch site	Cape Canaveral
Type	Discovery #01
Crew	Henry Hartsfield Michael Coats Richard Mullane Steven Hawley Charles Walker (first non astronaut) Judith Resnik
Landing date	5 Sep 1984
Landing site	Edwards
Payload	B: SBS 4 C: Leasat 2 D: Telstar 302

Flight of 6 days 56 min

OATS 1 mission


 STS 17

Also called STS 41G

General

Launch id	84108
Launch date	5 Oct 1984
Launch site	Cape Canaveral
Type	Challenger #06
Crew	Robert Crippen John McBride Kathryn Sullivan (first woman out in space) Sally Ride David Leetsma Paul Scully-Power Marc Garneau (Canada)
Landing date	13 Oct 1984
Landing site	Cape Canaveral
Payload	ERBS

Flight of 8 days 5 h 23 min

SIR C


 STS 19

Also called STS 51A

General

Launch id	84113
Launch date	8 Nov 1984
Launch site	Cape Canaveral
Type	Discovery #02
Crew	Frederik Hauck Joseph Allen David Walker Dale Gardner Anna Fisher
Landing date	16 Nov 1984
Landing site	Cape Canaveral
Payload	B: Anik D2 C: Leasat 1

Flight of 7 days 23 h 45 min

Palapa B2 and Westar 6 are brought back on Earth (were placed on a bad orbit by STS 11). Operation financed by the insurance companies.


 STS 20

Also called STS 51C

General

Launch id	85010
Launch date	24 Jan 1985
Launch site	Cape Canaveral
Type	Discovery #03
Crew	Thomas Mattingly Loren Shriver Ellison Onizuka James Buchli Gary Payton
Landing date	27 Jan 1985
Landing site	Cape Canaveral
Payload	B: USA 008

Flight of 3 days 1 h 33 min

DoD mission


 STS 23

Also called STS 51D

General

Launch id	85028
Launch date	12 Apr 1985
Launch site	Cape Canaveral
Type	Discovery #04
Crew	Karol Bobko Donald Williams David Griggs Margaret Seddon Jeffrey Hoffman David Mc Walker Jack Garn (senator)
Landing date	19 Apr 1985
Landing site	Cape Canaveral
Payload	B: Anik C1 C: Leasat 3

Flight of 6 days 23 h 55 min 20 s


 STS 24

Also called STS 51B

General

Launch id	85034
Launch date	29 Apr 1985
Launch site	Cape Canaveral
Type	Challenger #07
Crew	Robert Overmyer Frederik Gregory Don Lind William Thornton Taylor Wang Norman Thagard Lodewijk Vandenberg
Landing date	6 May 1985
Landing site	Edwards
Payload	B: Nusat 1 (radar calibration?) C: Glomr (couldn't be ejected)

Flight of 7 days 8 min

Spacelab 3 mission


 STS 25

Also called STS 51G

General

Launch id	85048
Launch date	17 Jun 1985
Launch site	Cape Canaveral
Type	Discovery #05
Crew	Daniel Brandestein John Creighton John Fabian Shannon Lucid Steven Nagel Patrick Baudry (France) Sultan Al Saud (Saudi Arabia)
Landing date	24 Jun 1985
Landing site	Edwards
Payload	B: Morelos 1 C: Arabsat 1B D: Telstar 303 E: Spartan 101-1 (launched and retrieved)

Flight of 7 days 1 h 38 min 53 s


 STS 26

Also called STS 51F

General

Launch id	85063
Launch date	29 Jul 1985
Launch site	Cape Canaveral
Type	Challenger #08
Crew	Story Musgrave Antony England John Bartoe Roy Bridges Karl Henise Loren Acton Gordon Fullerton
Landing date	6 Aug 1985
Landing site	Edwards
Payload	B: PDP (launched and retrieved)

Flight of 7 days 22 h 45 min 26 s. One of the 3 main motors stopped after 5 min 45 s. The shuttle was orbited 70 km below the nominal orbit

Spacelab 2 mission


 STS 26R

Also called STS 81A

General

Launch id	88091
Launch date	29 Sep 1988
Launch site	Cape Canaveral
Type	Discovery #07
Crew	R. Hauck Richard Covey John Lounge George Nelson David Hilmers
Landing date	3 Oct 1988
Landing site	Edwards
Payload	B: TDRS 3


 STS 27

Also called STS 51I

General

Launch id	85076
Launch date	27 Aug 1985
Launch site	Cape Canaveral
Type	Discovery #06
Crew	Joe Engle Richard Covey James Van Hoften William Fisher John Lounge
Landing date	3 Sep 1985
Landing site	Edwards
Payload	B: Optus A1 C: ASC 1 D: Leasat 4

Flight of 7 days 2 h 18 min 29 s

Leasat 3 was repared


 STS 27R

Also called STS 91A

General

Launch id	88106
Launch date	2 Dec 1988
Launch site	Cape Canaveral
Type	Atlantis #03
Crew	Robert Gibson Guy Gardner Rochard Mullane Jerry Ross William Sheperd
Landing date	6 Dec 1988
Landing site	Edwards
Payload	B: Lacrosse 1

Flight of 4 days 9 h

DoD mission


 STS 28

Also called STS 51J

General

Launch id	85092
Launch date	3 Oct 1985
Launch site	Cape Canaveral
Type	Atlantis #01
Crew	Karol Bobko Ronald Grabe David Hilmers Robert Stewart William Pailes
Landing date	7 Oct 1985
Landing site	Edwards
Payload	B: DSCS 3-03 C: DSCS 3-04

Flight of 4 days 1 h 45 min

DoD mission


 STS 28R

Also called STS 91D

General

Launch id	89061
Launch date	8 Aug 1989
Launch site	Cape Canaveral pad 39B
Type	Columbia #08
Crew	Brewster Shaw Richard Richards David Leetsma James Adamson Mark Brown
Landing date	13 Aug 1989
Landing site	Edwards
Payload	B: USA 040 C: USA 41

DoD mission


 STS 29

Also called STS 91B

General

Launch id	89021
Launch date	13 Mar 1989
Launch site	Cape Canaveral
Type	Discovery #08
Crew	Michel Coats John Blaha James Buchli Robert Springer James Bagion
Landing date	18 Mar 1989
Landing site	Edwards
Payload	B: TDRS 4


 STS 30

Also called STS 61A

General

Launch id	85104
Launch date	30 Oct 1985
Launch site	Cape Canaveral
Type	Challenger #09
Crew	Henry Hartsfield Steven Nagel James Buchli Guion Bluford Bonnie Dunbar Ernst Messerschmidt (Germany) Reinhardt Furrer (Germany) Wubbo Ockels (Netherlands)
Landing date	6 Nov 1985
Landing site	Edwards
Payload	B: Glomr (Global Low Orbiting Message Relay)

Flight of 7 days 44 min 51 s

Spacelab D1 mission (76 experiences including BIORAK)


 STS 30R

Also called STS 91C

General

Launch id	89033
Launch date	4 May 1989
Launch site	Cape Canaveral
Type	Atlantis #04
Crew	David Walker Ronald Grabe Norman Thagard Mary Cleave Mark Lee
Landing date	8 May 1989
Landing site	Edwards
Payload	B: Magellan


 STS 31

Also called STS 61B

General

Launch id	85109
Launch date	27 Nov 1985
Launch site	Cape Canaveral
Type	Atlantis #02
Crew	Brewster Shaw Brian O'Connor Mary Cleave Sherwood Springs Jerry Ross Charles Walker Rodolfo Vela (Mexico)
Landing date	3 Dec 1985
Landing site	Edwards
Payload	B: Morelos 2 C: Optus A2 D: Satcom K2

Flight of 6 days 21 h 4 min 50 s


 STS 31R

Also called STS 0E

General

Launch id	90037
Launch date	24 Apr 1990
Launch site	Cape Canaveral
Type	Discovery #10
Crew	Loren Shriver Charles Boden Steven Hawley Bruce Mc Candless Catherin Sullivan
Landing date	29 Apr 1990
Landing site
Payload	B: HST


 STS 32

Also called STS 61C

General

Launch id	86003
Launch date	12 Jan 1986
Launch site	Cape Canaveral pad 39A
Type	Columbia #07
Crew	Robert Gibson Charles Bolden Robert Cenker Steven Hawley George Nelson Franklin Chang-Diaz Bill Nelson
Landing date	18 Jan 1986
Landing site	Edwards
Payload	B: Satcom K1

Flight of 6 days 1 h 4 min 9 s

MSL 2


 STS 32R

Also called STS 0C

General

Launch id	90002
Launch date	9 Jan 1990
Launch site	Cape Canaveral pad 39A
Type	Columbia #09
Crew	Daniel Brandenstein James Wetherbee Bonnie Dunbar David Low Marsha Ivins
Landing date	20 Jan 1990
Landing site	Edwards
Payload	B: Leasat 5

Flight of 10 days 21 h 1 min

Retrieval of LDEF


 STS 33

Also called STS 51L

General

Launch date	28 Jan 1986
Launch site	Cape Canaveral
Type	Challenger #10
Crew	Francis Scobee Michael Smith Gregory Jarvis Judith Resnik Sharon Mc Auliffe Ronald Mc Nair Ellison Onizuka
Landing date
Landing site
Payload	TDRS 2 Spartan 203-1

Explosion after 73 s


 STS 33R

Also called STS 0B

General

Launch id	89090
Launch date	23 Nov 1989
Launch site	Cape Canaveral
Type	Discovery #09
Crew	Frederik Gregory David Griggs F. Story Musgrave Kathryn Thurnton Manley Carter
Landing date	28 Nov 1989
Landing site	Edwards
Payload	B: USA 48

DoD mission


 STS 34

Also called STS 0A

General

Launch id	89084
Launch date	18 Oct 1989
Launch site	Cape Canaveral
Type	Atlantis #05
Crew	Donald Williams Michael Mc Cully Shannon Lucid Ellen Baker Franklin Chang-Diaz
Landing date	23 Oct 1989
Landing site	Edwards
Payload	B: Galileo


 STS 35

General

Launch id	90106
Launch date	2 Dec 1990
Launch site	Cape Canaveral pad 39B
Type	Columbia #10
Crew	Brand Gardner Lounge Hoffman Parker Parise
Landing date	10 Dec 1990
Landing site	Edwards
Payload	none

ASTRO 1 mission


 STS 36

Also called STS 0D

General

Launch id	90019
Launch date	28 Feb 1990
Launch site	Cape Canaveral
Type	Atlantis #06
Crew	John Creighton John Casper Richard Mullane David Hilmers Pierre Thuot
Landing date	4 Mar 1990
Landing site	Edwards
Payload	B: KH 12-1

DoD mission


 STS 37

General

Launch id	91027
Launch date	5 Apr 1991
Launch site	Cape Canaveral
Type	Atlantis #08
Crew	Jerry Ross Jay Apt Linda Godwin Steven Nagel Henneth Cameron
Landing date	11 Apr 1991
Landing site	Edwards
Payload	B: GRO

Ross and Apt went out twice (5 h 46 min and 3 h 30 min) to free GRO's antenna


 STS 38

General

Launch id	90097
Launch date	15 Nov 1990
Launch site	Cape Canaveral
Type	Atlantis #07
Crew	Covey Culbertson Springer Meade Gemar
Landing date	20 Nov 1990
Landing site	Cape Canaveral
Payload	USA 067

DoD mission


 STS 39

General

Launch id	91031
Launch date	28 Apr 1991
Launch site	Cape Canaveral
Type	Discovery #12
Crew	Donald Mc Monagle Blaine Hammond Charles Veach Guion Bluford Michael Coats Gregory Harbaugh Richard Hieb
Landing date	6 May 1991
Landing site	Cape Canaveral
Payload	B: IBSS (launched and retrieved) C: Mpec (USA 70)

Flight of 8 days 7 h 26 min

DoD mission


 STS 40

General

Launch id	91040
Launch date	5 Jun 1991
Launch site	Cape Canaveral pad 39B
Type	Columbia #11
Crew	James Bagian Bryan O'Connor Drew Gaffney Sidney Gutierrez Margareth Rhea Seddon Millie Hughes-Fulford Tamara Jernigan
Landing date	14 Jun 1991
Landing site	Edwards
Payload	none

Flight of 9 days 3 h 30 min

SLS 1 (Space Laboratory Science) mission


 STS 41

General

Launch id	90090
Launch date	6 Oct 1990
Launch site	Cape Canaveral
Type	Discovery #11
Crew	Richard Richards Robert Parker Bruce Melnick William Shepperd Thomas Akers
Landing date	10 Oct 1990
Landing site	Edwards
Payload	B: Ulysses


 STS 42

General

Launch id	92002
Launch date	22 Jan 1992
Launch site	Cape Canaveral
Type	Discovery #14
Crew	Grabe Oswald Thagard Readdy Hilmers Roberta Bondar (Canada) Ulf Merbold (Germany)
Landing date	30 Jan 1992
Landing site	Edwards
Payload	none

Flight of 8 days 1 h 14 min

IML 1 mission


 STS 43

General

Launch id	91054
Launch date	2 Aug 1991
Launch site	Cape Canaveral
Type	Atlantis #09
Crew	John Blaha Michael Baker James Adamson David Low Shannon Lucid
Landing date	11 Aug 1991
Landing site	Cape Canaveral
Payload	B: TDRS 5


 STS 44

General

Launch id	91080
Launch date	25 Nov 1991
Launch site	Cape Canaveral
Type	Atlantis #10
Crew	Gregory Henricks Voss Musgrave Runco Hennen
Landing date	1 Dec 1991
Landing site	Edwards
Payload	DSP 3-4

DoD mission


 STS 45

General

Launch id	92015
Launch date	24 Mar 1992
Launch site	Cape Canaveral
Type	Atlantis #11
Crew	Bolden Duffy Leetsma Sullivan Foale Lichtenberg Dirck Frimout (Belgium)
Landing date	2 Apr 1992
Landing site	Cape Canaveral
Payload	none

ATLAS 1 mission


 STS 46

General

Launch id	92049
Launch date	31 Jul 1992
Launch site	Cape Canaveral
Type	Atlantis #12
Crew	Shriver Allen Nicollier Ivins Chang_Diaz Hoffman Malerba
Landing date	8 Aug 1992
Landing site	Cape Canaveral
Payload	B: Eureca 1

Tried to deploy TTS 1


 STS 47

General

Launch id	92061
Launch date	12 Sep 1992 at 14:23 UT
Launch site	Cape Canaveral, pad 39A
Type	Endeavour #02
Crew	Robert Gibson Brown Lee Jerome Apt Jan Davis Mae Jemison Mamoru Mohri (Japanese)
Landing date	20 Sep 1992 at 14:53 UT
Landing site	Cape Canaveral
Payload	none

Spacelab J mission


 STS 48

General

Launch id	91063
Launch date	12 Sep 1991
Launch site	Cape Canaveral
Type	Discovery #13
Crew	Creighton Reightler Gemar Brown Buchli
Landing date	18 Sep 1991
Landing site	Edwards
Payload	B: UARS


 STS 49

General

Launch id	92026
Launch date	7 May 1992
Launch site	Cape Canaveral
Type	Endeavour #01
Crew	Brandenstein Chilton Melnick Thornton Pierre Thuot Richard Hieb Thomas Aker
Landing date	16 May 1992
Landing site	Edwards
Payload	none

Astronauts went out during 8 h 29 min on 13 May 1992 to repair Intelsat 603


 STS 50

General

Launch id	92034
Launch date	25 Jun 1992
Launch site	Cape Canaveral pad 39A
Type	Columbia #12
Crew	Richards Bowersox Dunbar Baker Meade Delucas Trinh
Landing date	9 Jul 1992
Landing site	Cape Canaveral
Payload	none

USML 1 mission


 STS 51

General

Launch id	93058
Launch date	12 Sep 1993
Launch site	Cape Canaveral
Type	Discovery #17
Crew	5 persons
Landing date	22 Sep 1993
Landing site	Cape Canaveral
Payload	B: ACTS C: Orfeus-Spas (launched and retrieved)


 STS 52

General

Launch id	92070
Launch date	22 Oct 1992
Launch site	Cape Canaveral pad 39B
Type	Columbia #13
Crew	Wetherbee Baker Jernigan Veach Shepherd Mc Learn
Landing date	1 Nov 1992
Landing site	Cape Canaveral
Payload	B: Lageos 2 C: CTA (launched and retrieved)

USMP 1 mission


 STS 53

General

Launch id	92086
Launch date	2 Dec 1992
Launch site	Cape Canaveral
Type	Discovery #15
Crew	Walker Cabana Bluford Voss Clifford
Landing date	9 Dec 1992
Landing site	Edwards
Payload	B: USA 089

DoD mission


 STS 54

General

Launch id	93003
Launch date	13 Jan 1993 at 13:59:30 UT
Launch site	Cape Canaveral, LC39B
Type	Endeavour #03
Crew	John Casper Donald Mc Monagle Gregory Harbaugh Mario Runco Susan Helms
Landing date	19 Jan 1993
Landing site	Cape Canaveral
Payload	B: TDRS 6

PARE (Physiological and Anatomical Rodent Experiment) experiment


 STS 55

General

Launch id	93027
Launch date	26 Apr 1993 at 14:50 UT
Launch site	Cape Canaveral pad 39A
Type	Columbia
Crew	Steven Nagel Terence Henricks Jerry Ross Charles Precourt Bernard Harris Ulrich Walter (Germany) Hans William Schlegel (Germany)
Landing date	6 May 1993 at 14:30 UT
Landing site	Edwards
Payload	none

Spacelab D2 mission


 STS 56

General

Launch id	93023
Launch date	8 Apr 1993
Launch site	Cape Canaveral
Type	Discovery #16
Crew	Cameron Oswald Foale Cockrell Ochoa
Landing date	17 Apr 1993 at 11:37 UT
Landing site	Cape Canaveral
Payload	B: Spartan 201-1 (launched and retrieved)

ATLAS 2 mission


 STS 57

General

Launch id	93037
Launch date	21 Jun 1993 at 13:07 UT
Launch site	Cape Canaveral
Type	Endeavour #04
Crew	Grabe Duffy Low Sherlock Wisoff Voss
Landing date	1 Jul 1993 at 12:52 UT
Landing site	Cape Canaveral
Payload	none

Spacehab 1 (SH 1) mission

Retrieval of Eureca


 STS 58

General

Launch id	93065
Launch date	18 Oct 1993
Launch site	Cape Canaveral pad 39B
Type	Columbia #15
Crew	Blaha Searfoss Seddon Mc Arthur Wolf Lucid Fettman
Landing date	1 Nov 1993 at 10:05 UT
Landing site	Edwards
Payload	none

SLS 2 mission


 STS 59

General

Launch id	94020
Launch date	9 Apr 1994 at 12:05 UT
Launch site	Cape Canaveral
Type	Endeavour #06
Crew	At least: Dr. Jay Apt (N5QWL), commander Dr. Linda Godwin (N5RAX), specialist
Landing date	20 Apr 1994 at 17:54 UT
Landing site	Edwards
Payload

SRL 1 and SAREX missions

It carried synthetic aperture radars at three wavelengths: 23 cm (C-band), 6 cm (C-band), and 3 cm (X-band). For each wavelength, there was an array of six, electronically steerable antenna panels; the polarization plane of the emitted radiation could be varied as needed. It was expected to cover 46 million square kilometers of terrain and vegetation, yielding 32 trillion bits of data for capturing in 183 high-density tapes on board.


 STS 60

General

Launch id	94006
Launch date	3 Feb 1994 at 12:10 UT
Launch site	Cape Canaveral
Type	Discovery #18
Crew	7 persons (1 woman)
Landing date	11 Feb 1994
Landing site
Payload	B: Oderacs 1A C: Oderacs 1B D: Oderacs 1C E: Oderacs 1D F: Oderacs 1E G: Oderacs 1F H: Bremsat

On board was the Spacehab 2 (SH 2) facility to conduct 12 experiments. Among them were the following four GAS (Get Away Special) microgravity experiments: G-536--Pool Boiling experiment; G-557--Capillary Pumped Loop experiment; G-071--Ball Bearing experiment; and G-514--Orbiter Stability experiment. It also carried resources for high school/college science experiments.

Repeated efforts to deploy a three-meter diameter, retrievable shield (Wake Shield Facility) behind which pure crystals of Gallium Arsenide were planned to be grown were unsuccessful.


 STS 61

General

Launch id	93075
Launch date	2 Dec 1993
Launch site	Cape Canaveral
Type	Endeavour #05
Crew	Covey Bowerbox Akers Hoffman Musgrave Thornton Nicollier
Landing date	13 Dec 1993
Landing site	Cape Canaveral
Payload	none

Reparation of Hubble


 STS 62

General

Launch id	94015
Launch date	4 Mar 1994
Launch site	Cape Canaveral
Type	Columbia #16
Crew	Casper Allen Thuot Geman Ivins
Landing date	18 Mar 1994
Landing site	Cape Canaveral
Payload

It carried a U.S. Microgravity Payload (USMP 2) and an Office of Aeronautics and Space Technology Second payload (OAST 2). Among the experiments were the Solar Array Module Plasma Interaction Experiment (SAMPIE), the Thermal Energy Storage (TES) experiment, the Experimental Investigation of Spacecraft Glow (EISG) experiment, the Spacecraft Kinetic InfraRed Test (SKIRT) experiment, the Emulsion Chamber Technology (ECT) experiment, and the CRYOgenic Two Phase (CRYOTP) experiment. A new high-speed, Ku-band communication link between mission control and the shuttle enabled transmission of 162 megabytes of data.


 STS 63

General

Launch id	95004
Launch date	3 Feb 1995 at 05:22:04 UT
Launch site	Cape Canaveral LC39B
Type	Discovery #20
Crew	Jim Wetherbee (commander) Eileen Collins (pilot) Bernard Harris (mission specialist) Mike Foale (mission specialist) Janice Voss (mission specialist) Vladimir Titov (Russian Space Agency)
Landing date	Cape Canaveral
Landing site	11 Feb 1995 at 11:50 UT
Payload	Spartan 201-2 (launched and retrieved) Oderacs 2A Oderacs 2B Oderacs 2C Oderacs 2D Oderacs 2E Oderacs 2F

Spacehab 3 (SH 03) mission

The Spacehab module is a pressurized laboratory containing experiment racks and lockers. FU-1 has a new window in the roof to help in the Mir rendezvous operation.

It carried the Spacehab module containing microgravity experimental apparatus. Despite a thruster leak from the shuttle, STS 63 was finally allowed to come close to the MIR station, within about twelve meters, as a prelude to a planned docking in the future.

This was the second time there had been three women in space (STS 40 was the first), and the second time that a Russian had flown on a US spaceship.


 STS 64

General

Launch id	94059
Launch date	9 Sep 1994 at 22:22 UT
Launch site	Cape Canaveral, pad 39B
Type	Discovery #19
Crew	Richard (Dick) Richards, commander L. Blaine Hammond Jr. (KC5HBS), pilot Jerry L. Linenger (KC5HBR) Susan Helms Carl Meade Mark Lee
Landing date	20 Sep 1994
Landing site
Payload	Spartan 204-1 (launched and retrieved)

Lidar In-Space Technology Experiment (LITE 1) and SAREX

Also on board were 12 Get Away Special (GAS) experiments designed and built by high school and university students, an Orbit Stability Experiment (OSE), and a Robot Operated Materials Processing System (ROMPS).

Lidar is essentially radar using an optical wavelength laser instead of microwaves. LITE consists of a Spacelab pallet with a laser transmitter and a receiver telescope. In an interesting historical note, the 96-cm receiver telescope was built in the 1960s as the engineering model for the telescope on the OAO-B satellite, lost in a 1970 launch failure. It was refurbished for the LITE mission.

LITE 1 results (made from the June 16 issue of RESEARCHER NEWS, Langley Research Center)

According to Dr. M. Patrick McCormick, LITE project scientist and branch head of Langley's Aerosol Research Branch, the LITE mission was 100 percent successful. One mission highlight was the collection of spectacular data on Super Typhoon Melissa. From the cargo bay of Space Shuttle Discovery, LITE passed directly over the eye of the typhoon and profiled the eye-wall clouds from the top to the sea surface below.

Unlike passive instruments which measure the amount of heat emitted or light reflected by only the highest layer of multi-layered clouds, LITE is able to penetrate the highest clouds and provide scientists with data about clouds at many levels below. The LITE data also revealed high cirrus clouds which were not seen in the standard meteorological satellite data and are often not expressed in atmospheric models.

Using the three different wavelengths aboard LITE also allowed Browell [Dr. Edward Browell is a senior scientist in Langley's Chemistry and Dynamics Branch] and his team to identify the types of aerosols they were measuring. Browel said, "Remotely, we can detect whether the aerosols we're seeing are biomass burning or whether they're desert aerosols (sands)." Biomass burning generates green-house gases such as carbon dioxide, methane and ozone. Aerosols also affect the Earth's energy budget by scattering sunlight back into space, thereby cooling the Earth. Aerosols can also increase the amount of clouds present by acting as surfaces upon which water vapor can condense.

The LITE system obtained a spectacular data set, demonstrating the ability of lidar remote sensing techniques to study the Earth's atmosphere. A future space-based lidar system is being studied. This future system would fly on a satellite in low-earth orbit and provide daily coverage of global cloud characteristics and aerosols created by dust storms, biomass burning and urban pollution.


 STS 65

General

Launch id	94039
Launch date	8 Jul 1994 at 16:43 UT
Launch site	Cape Canaveral pad 39A
Type	Columbia #17
Crew	Robert D. Cabena (KC5HBV), commander James Halsell, pilot Richard Hieb Carl Walz Leroy Chiao Donald Thomas Chiaki Naito, cardiolog (first Japanese woman in space)
Landing date	23 Jul 1994 at 10:38 UT
Landing site	Cape Canaveral
Payload

Spacelab IML 2 and SAREX. On board were six goldfish, four Japanese Medeka fish, four red-bellied newts, 500 fruit flies, 126 jelly fish, and thousands of sea urchins.


 STS 66

General

Launch id	94073
Launch date	3 Nov 1994 at 06:59 UT
Launch site	Cape Canaveral
Type	Atlantis #13
Crew	1 ESA astronaut
Landing date	14 Nov 1994
Landing site	Edwards
Payload	Spas 4 (launched and retrieved)

Atmospheric Lab (Atlas 3)

The primary payload was the ATLAS 3 laboratory containing two instruments (SOLCON and SOLSPEC) to measure solar emissions in the visible and UV bands, and a UV backscatter monitor to measure ozone concentrations. The shuttle also carried many pregnant and nonpregnant rats for biological studies.

MAS, a German instrument which was ATLAS 3's only sensor capable of measuring chlorine monoxide (a crucial intermediate in CFCs' effect on ozone), died after only about six hours of operation.


 STS 67

General

Launch id	95007
Launch date	2 Mar 1995 at 06:38:14 UT
Launch site	Cape Canaveral LC39A
Type	Endeavour #08
Crew	Steve Oswald (commander) William Gregory (pilot, KC5MGA) Tamara Jernigan (payload commander, KC5MGF) Wendy Lawrence (mission specialist) John Grunsfeld (mission specialist) Ron Parise (payload specialist, Computer Sciences Corp.) Sam Durrance (Johns Hopkins University)
Landing date	18 Mar 1995 at 21:47:00 UT
Landing site	Edwards
Payload

Ultraviolet Astronomy (ASTRO 2) mission

New endurance record: 16 days 15 hours 9 min 46 s

School groups in 26 places around the world made voice contacts with the STS 67 crew as part of the Shuttle Amateur Radio EXperiment (SAREX) component of this mission.

Astro 2 is a Spacelab mission, using two Spacelab Pallets with the Spacelab Igloo avionics container and the IPS instrument pointing system. Mounted on the IPS are three ultraviolet telescopes. The 0.9-m Hopkins Ultraviolet Telescope (HUT) takes spectra in the 900 to 1900 Angstrom short wavelength UV range and the 500 to 900 A extreme ultraviolet range. The 0.5m Wisconsin Ultraviolet Photo-Polarimeter Experiment (WUPPE) telescope studies spectra in the longer wavelength 1400-3200A ultraviolet range. The 0.38m Ultraviolet Imaging Telescope (UIT) is a wide-field (0.6 degree) imaging telescope which uses ultraviolet-sensitive film.

Also in the cargo bay are the Extended Duration Orbiter (EDO) pallet and two Getaway Special (GAS) cans (G-387/G-388) which constitute the Endeavour Telescope, a project of the Australian Space Office. The 0.1m telescope takes a narrow-band, 2-degree wide-field ultraviolet image. Unlike UIT, it uses CCDs rather than film. The Australian Endeavour telescope first flew (as G-609/G-610) aboard Discovery in Jan 1992, but failed to work correctly. On that mission it was attached to a cross-bay GAS Bridge Assembly (GBA) with other GAS cans; this time the cans are mounted on a GAS Beam Adapter (GABA) on the side of the payload bay wall.


 STS 68

General

Launch id	94062
Launch date	30 Sep 1994
Launch site	Cape Canaveral
Type	Endeavour #07
Crew
Landing date	11 Oct 1994
Landing site	Edwards
Payload

SRL 2 mission

It carried the Space Radar Laboratory (SRL) containing SIR-C, a dual polarization radar at C- and L-bands, X-SAR, an X-band vertical polarization radar, and MAPS, an infrared sensor for measurement of air pollution.


 STS 69

General

Launch id	95048
Launch date	7 Sep 1995 at 15:09 UT
Launch site	Cape Canaveral LC39A
Type	Endeavour #09
Crew	David Walker (Commander) Ken Cockrell (Pilot) James Voss (Payload Commander) James Newman (Mission Specialist) Michael Gernhardt (Mission Specialist)
Landing date	18 Sep 1995 at 11:37 UT
Landing site	Cape Canaveral
Payload	Spartan 201-3 WSF 2

WSF 2 and the IEH astronomy experiment

Also on board: a GAS Bridge Assembly with four standard GAS can experiments, plus the CAPL Hitchhiker experiment to test a cooling system for EOS satellites and the Thermal Energy Storage (TES) GAS can experiment to do research on solar dynamic power for the Space Station.


 STS 70

General

Launch id	95035
Launch date	13 Jul 1995 at 13:41:55 UT
Launch site	Cape Canaveral LC39B
Type	Discovery #21
Crew	Tom Henricks (commander) Kevin Kregel (pilot) Nancy Currie (mission specialist) Dr. Donald Thomas (mission specialist) May Ellen Weber (mission specialist)
Landing date	22 Jul 1995 at 12:02 UT
Landing site	Cape Canaveral
Payload	B: TDRS 7

STS-70 marked another significant milestone with the first flight of the new Block I Space Shuttle main engine. Main Engine #1 - engine 2036 - features improvements that increase the reliability and safety margins of the main engines. SSME's No. 2 and No. 3 are the current design.

The Block I engine features improvements such as a new liquid oxidizer turbopump produced through a casting process that eliminates all but six of the 300 welds that exist in the current pump. A new two-duct powerhead improves fluid flows within the engine to decrease pressure and loads. A new single-coil heat exchanger in the powerhead eliminates all seven weld joints inside the engine, reducing wear, maintenance and post-flight inspections.


 STS 71

General

Launch id	95030
Launch date	27 Jun 1995 at 19:32 UT
Launch site	Cape Canaveral LC39A
Type	Atlantis #14
Crew
Landing date	7 Jul 1995 at 14:54 UT
Landing site	Cape Canaveral
Payload

Space Life Sciences (SL M) and first trim with Mir


 STS 73

General

Launch id	95056
Launch date	20 Oct 1995 at 13.53 UT
Launch site	Cape Canaveral LC39B
Type	Columbia #18
Crew
Landing date	5 Nov 1995 at 11:45 UT
Landing site	Cape Canaveral
Payload

Spacelab USML-2


 STS 74

General

Launch id	95061
Launch date	12 Nov 1995 at 12:30 UT
Launch site	Cape Canaveral LC39A
Type	Atlantis #15
Crew
Landing date	20 Nov 1995 at 17:01 UT
Landing site	Cape Canaveral
Payload	316GK Mir docking modules and supplies

2nd Mir docking


 STS 72

General

Launch id	96001
Launch date	11 Jan 1996 at 09:41 UT
Launch site	Cape Canaveral LC39B
Type	Endeavour #10
Crew	Brian Duffy Brent Jett Leroy Chiao Winston Scott Koichi Wakata (NASDA) Daniel Barry
Landing date	20 Jan 1996 at 07:42 UT
Landing site	Cape Canaveral
Payload	Spartan 206-1

SFU retrieval on 13 January

2 spacewalks to test out Space Station tools and equipment.


 STS 75

General

Launch id	96012
Launch date	22 Feb 1996 at 11:24 UT
Launch site	Cape Canaveral
Type	Columbia #19
Crew	Andrew Allen (commander) Dr. Scott Horowitz (pilot) Dr. Franklin Chang-Diaz (payload commander) Dr. Jeff Hoffmann (mission specialist) Claude Nicollier (mission specialist, ESA) Maurizio Cheli (mission specialist, ESA) Dr. Umberto Guidoni (mission specialist, ASI)
Landing date	9 Mar 1996
Landing site	Cape Canaveral
Payload

Deployment of the TTS 2 (first was on STS 46) also known as TSS 1R. Third flight of scientific investigations using the US Microgravity Payload (USMP) complement.


 STS 76

General

Launch id	96018
Launch date	22 Mar 1996
Launch site	Cape Canaveral
Type	Atlantis #16
Crew	Kevin Chilton (commander) Rick Searfoss (pilot) Ron Sega (payload commander) Linda Godwin (mission specialist) RichClifford (mission specialist) Shannon Lucid (mission specialist, to remain on Mir)
Landing date
Landing site
Payload

3rd Shuttle-Mir mission, Spacehab, SAREX


 STS 77

General

Launch id
Launch date	planned on 25 Apr 1996
Launch site	Cape Canaveral
Type	Endeavour #11
Crew	John H. Casper: commandant Curtis L. Brown: pilot Daniel W. Bursch: mission specialist Mario Runco: mission specialist Marc Garneau (Canadian space agency): mission specialist Andrew S.W. Thomas: mission specialist
Landing date
Landing site
Payload	Spartan 207-1

Spacehab 4

will carry the Spacehab module, which nearly triples the amount of middeck locker space available for experiments. The Shuttle-Pointed Autonomous Research Tool for Astronomy (SPARTAN) satellite will be deployed and retrieved during the mission.


 STS 78

General

Launch id
Launch date	planned on 27 Jun 1996
Launch site	Cape Canaveral
Type	Columbia #20
Crew	7 Susan J. Helms: mission specialist Richard M. Linnehan: mission specialist Charles E. Brady: mission specialist Jean-Jacques Favier (France, CEA/CNES): payload specialist Robert Brent Thirsk (Canadian space agency): payload specialist
Landing date	16-day flight
Landing site
Payload

Spacelab, life and microgravity Spacehab (LMS), SAREX

See NASA-212.94.TXT


 STS 79

General

Launch id
Launch date	planned on 1 Aug 1996
Launch site	Cape Canaveral
Type	Atlantis #17
Crew
Landing date
Landing site
Payload

Mir docking 4, SAREX


 STS 80

General

Launch id
Launch date	planned on 7 Nov 1996
Launch site	Cape Canaveral
Type	Columbia #21
Crew
Landing date
Landing site
Payload	Spas 3

WSF 3, SAREX


 STS 81

General

Launch id
Launch date	planned on 5 Dec 1996
Launch site	Cape Canaveral
Type	Atlantis #18
Crew
Landing date
Landing site
Payload

Mir docking 5, SAREX


 STS 82

General

Launch id
Launch date	planned for 13 Feb 1997
Launch site	Cape Canaveral
Type	Discovery #22
Crew	Mark C. Lee Gregory J. Harbaugh Steven L. Smith Joseph R. Tanner
Landing date	16-day flight
Landing site
Payload

second flight to service the Hubble Space Telescope

The mission plan, planned to include at least three spacewalks, currently includes changeout of two science instruments and a data interface unit. The instruments are the Space Telescope Imaging Spectrograph and the Near Infrared Camera Multi-Object Spectrometer.


 Taurus

Jean-Jacques Serra

In 1989 OSC was selected by DARPA to design the Standard Small Launch Vehicle (SSLV). This solid 4-stage rocket called Taurus is made of the first stage of the MX and the 3 stages of Pegasus. The base stage, called stage-0, is a Thiokol TU 903 of 8.4 m long, 2.34 m diameter and 48 tons. It delivers the 3 Pegasus stages at 38000 m altitude at 2030 m/s.

In the future (standard type), the stage-0 will be a Thiokol Castor 120 which is a MX motor modified to provide a weaker acceleration (6.5 G max). Taurus is 27.5 m in height and can launch 1.36 tons in LEO.

Taurus versions

Prototype	Taurus
Standard Type (with Castor-120)	Taurus-120
stretched standard type	Taurus-120XL
stretched standard type with strap-ons	Taurus-120XL/S
Taurus launches

#	Launch id	Payload	Launch Date	Site	Type	Status/Comment (orbit in perigee x apogee x inclination x period)
1	94017	A: USA 101 B: USA 102	13 Mar 1994 at 22:32 UT	V 576E		540 km x 560 km x 105°


Thor (launch vehicle)
 Thor

Jean-Jacques Serra

Origins

Thor Able

Thor Ablestar

Thor Agena

Thor Delta

Thor with solid top stage (Altair, Burner)

Origin: first generation of American Intermediate Range Ballistic Missiles

Until 1953 the USAF had stressed on aerodynamic missiles (while the Army was developping the Jupiter) because they believed long distance ballistic missiles would not appear before ten years. The construction of Thor wasn't awarded to Douglas Aircraft before December 1955. The program was given a very high priority and the first missile was delivered to the USAF in October 1956.

The MB-1 propulsion system was made of a Rocketdyne LR79 (liquid oxygen and kerosene) engine with 68 tons thrust derived from Jupiter and Atlas' booster. An LR101 vernier rocket on each side of the missile' base controled the roll and the final ajustement of the speed after the main engine shutdown. The missile used Atlas' Reentry Vehicle, measured 2.44 m in diameter and 19.8 m in height, and weighed over 46 tons.

The first four tests carried out from 25 January 1957 on were failures. The first successful launch occured on 20 September and was commissioned in 1959.

Thor's propulsion system quickly evolved to an MB-3 version used by IRBMs and space launchers, especially by USAF's Thor SLV-2 and NASA's Thor Delta launchers. In the seventies the MB-3 motor was used by the Japanese N-1, N-2 and H-1 launch vehicles. An improvement program conducted between 1957 and 1959 named X-1 leaded to an H-1 version designed for Saturn-1. Later on H-1 was modified for the propulsion of Thor Deltas (39xx series) and became RS-27. The latest version RS-27A intended to Delta-2 launchers is optimized for greater performance at high altitude.

Thor propulsion system [chart 1]

Designation	Year of first launch	Main engine Thrust (ton)	Main engine SI (sec.)	Application
MB-1	1957	61.2	250	IRBM
MB-3	1958	68, 75, 77 (1)	252	IRBM, launchers
RS-27	1973	93.7-104.6 (2)	263-295 (2)	Delta
RS-27A	1991	90.6-107.4 (2)	255-305 (2)	Delta-2

Notes: (1) Blk 1, 2 and 3; (2) values given at sea level in vacuum

In 1963 Thor's thrust became insufficient to carry out its missions. The solution (innovative at that time) found was to enhance it with 3 solid fuel strap on Thiokol Castor boosters. This resulted in TAT: Thrust Augmented Thor. The 79 cm-diameter motor of these boosters, which derived from the Sergeant tactical missile, was used as Scout's second stage. The Castor-1 boosters delivered about 24 tons thrust during 30 seconds; Castor-2 delivered 25 tons during 38 seconds. Those boosters were used grouped by 3 then 6 and up to 9. After 1975 when the only Thor first stage used was the Delta the Castor-2 boosters were replaced by the 1 m-diameter Castor-4.

The burn duration of Thor was also enhanced by lenghtening its tanks. This gave birth to the LTT (Long Tank Thor) in 1966 with Agena stages and in 1968 with Delta stages. The first stage was further lengthened in 1989 for Delta-2.


Thor

[launch vehicle index]

Origins

Thor Able

Thor Ablestar

Thor Agena

Thor Delta

Thor with solid top stage (Altair, Burner)


 Thor Able

Jean-Jacques Serra

Gunter Krebs (listing)

Thor used with Vanguard top stages

In 1958 the only top stages available for space launches were those of Vanguard. The second stage was 8.5 m long and 0.9 m in diameter. It was equipped with an adjustable Aerojet AJ10 motor (nitric acid/UDMH) capable of a 3.4 ton thrust during 120 seconds. The spin-stabilized third stage was equipped with a solid fuel motor of 1.1 ton thrust and 30 second burn duration. The Thor Able rocket was 26.9 m high and weighed over 50 tons.

Thor Able was tested in April and May 1958 with the intercontinental launch of Reentry vehicles containing a mouse. But the first 3 space launches carrying Pioneer probes to the Moon between August and November 1958 ended as 2 failures and 1 partial success.

The launcher was used until 1961 to launch a scientific satellite (Explorer) a interplanetary probe (Pioneer) and a meteorological satellite (Tiros).

Thor Able launches [chart 2]

# and serial	Launch id	Payload	Launch date	Type	Status (orbit in perigee x apogee x inc. x period)
1, 116	n/a	ARTV 1 (suborbital)	23 Apr 1958	DM18 Able	Failure: Thor exploded after 146 s
2, 118	n/a	ARTV 2 (suborbital)	10 Jul 1958	DM18 Able
3, 119	n/a	ARTV 3 (suborbital)	23 Jul 1958	DM18 Able
4, 127	n/a	Pioneer 0 (Moon)	17 Aug 1958	DM18 Able 1	Failure: Thor exploded after 17 s
5, 130	n/a	Pioneer 1 (Moon)	11 Oct 1958	DM18 Able 1	Partial failure: 3rd stage produced unsufficient thrust
6, 129	n/a	Pioneer 2 (Moon)	08 Nov 1958	DM18 Able 1	Failure: 3rd stage failed
7, 128	n/a	PGRTV 1 (suborbital)	23 Jan 1959	DM18 Able 2	Partial failure: 1st stage shut down at wrong time
8, 131	n/a	PGRTV 2 (suborbital)	28 Feb 1959	DM18 Able 2
9, 132	n/a	PGRTV 3 (suborbital)	21 Mar 1959	DM18 Able 2
10, 133	n/a	PGRTV 4 (suborbital)	8 Mar 1959	DM18 Able 2
11, 135	n/a	PGRTV 5 (suborbital)	20 May 1959	DM18 Able 2
12, 137	n/a	PGRTV 6 (suborbital)	11 Jun 1959	DM18 Able 2
13, 134	59004	Explorer 06	07 Aug 1959	DM18 Able 3
14, 136	n/a	Transit 1A	17 Sep 1959	DM18 Able 2	Failure: 3rd stage failed
15, 219	60001	Pioneer 5	11 Mar 1960	DM18 Able 4	Probe to solar orbit
16, 148	60002	Tiros 01	01 Apr 1960	DM18 Able 2

Notes: all launches from Cape Canaveral


 Thor Ablestar

Jean-Jacques Serra

Gunter Krebs (listing)

The Ablestar stage was developped for the US Navy by Space General Co. It was 5.3 m long and 1.63 m in diameter, equipped with an adjustable Aerojet AJ10-104 motor (nitric acid/UDMH). This engine could be reignited and provided a 3.5 ton thrust during about 300 seconds. Thor Ablestar was 24.2 m high for about 54 tons.

Thor Ablestar was used to launch navigation satellites (Transit) so as numerous technologic and scientific spacecrafts (Solrad) for the US Navy. Some satellites were launched together with NASA. Thor Ablestar was used during 5 years and achieved the first in-orbit reignition in April 1960 and the first double, triple and sextuple -satellite launch.

Thor Ablestar launches [chart 3]

# and serial	Launch id	Payload	Launch date	Site	Type	Status (orbit in perigee x apogee x inc. x period)
1, 257	60003	Transit 1B	13 Apr 1960	C	DM21 AbleStar	373 x 748 x 51.3 x 95.8
2, 281	60007	Transit 2A Solrad 01	22 Jun 1960	C	DM21 AbleStar
3, 262	n/a	Courier 1A	18 Aug 1960	C	DM21 AbleStar	Failure: Thor failed after 134 s
4, 293	60013	Courier 1B	04 Oct 1960	C	DM21 AbleStar
5, 283	n/a	Transit 3A Solrad 2	30 Nov 1960	C	DM21 AbleStar	Failure: Thor shud down too early
6, 313	61007	Transit 3B LOFTI	22 Feb 1961	C	DM21 AbleStar	Partial failure: satellites failed to separate 188 x 822 x 28.4 x 96.2
7, 315	61015	Transit 4A Solrad 03	29 Jun 1961	C	DM21 AbleStar	Partial failure: Injun 1 and Solrad 3 failed to separate
8, 305	61031	Transit 4B Traac	15 Nov 1961	C	DM21 AbleStar
9, 311	n/a	Lofti 2 Secor 1 Solrad 4 Surcal 1	24 Jan 1962	C	DM21 AbleStar	Failure: AbleStar produced unsufficient thrust Surcal 1 was fixed to AbleStar
10, 314	n/a	Anna 1A	10 May 1962	C	DM21 AbleStar	Failure: AbleStar failed to ignite
11, 319	62060	Anna 1B	31 Oct 1962	C	DM21 AbleStar
12, 375	63038	Transit 5BN1 5E1	28 Sep 1963	V	DM21 AbleStar
13, 385	63049	Transit 5BN2 5E3	05 Dec 1963	V	DM21 AbleStar
14, 379	n/a	Transit 5BN3	21 Apr 1964	V	DM21 AbleStar	Failure: AbleStar failed
15, 250	64063	Transit-O 1 (OPS 5798, NNS 30010) Calsphere 1 & 2	06 Oct 1964	V	DM21 AbleStar	1035 x 1080 x 89.9 x 106.6
16, 423	64083	Transit-O 2 (OPS 6582 NNS 30020) 5E5	13 Dec 1964	V	DM21 AbleStar	1027 x 1086 x 90 x 106.3
17, 440	65017	Transit-O 3 (OPS 7087 NNS 30030) Secor 02	11 Mar 1965	V	DM21 AbleStar
18, 447	65048	Transit-O 4 (OPS 8480, NNS 30040)	24 Jun 1965	V	DM21 AbleStar	1025 x 1114 x 90 x 106.9
19, 455	65065	Transit-O 5 (OPS 8464, NNS 30050) Surcal (x3?) Dodecapole 2 Tempsat 1	13 Aug 1965	V	DM21 AbleStar	1089 x 1194 x 90 x 108.2

Notes: in the launcher date & site column C stands for Cape Canaveral and V for Vandenberg.


 Thor Agena

Jean-Jacques Serra

Gunter Krebs (listing)

The Agena stage was developped by Lockheed for the USAF. The first Thor Agena (with Discoverer 1) was 23.2 m in height and weighed 48.5 tons. This version was Agena-A equipped with a Bell 8096 motor of 6.8 t thrust during 2 minutes. It couldn't be re-ingnite on the contrary of the 1960 Agena-B. The Agena-D version featured a more powerful engine with 7.25 tons thrust delivered during 4 minutes. All those rockets had the same diameter (1.52 m) and a variable length depending on the payload.

Agena was used from 1959 to 1987 becoming the most used American top-stage with 350 launches mainly with military payloads:

- reconnaissance satellites (Discoverer, Keyhole) sometimes orbited with military payloads (Ferret) or civilian payloads (Oscar).

- ELINT satellites: large ones were launched as unique payload and small size ones together with reconnaissance satellites.

But Thor Agena also launched:

- scientific satellites (Solrad, Starad, STP), geodesy satellites (Secor, Starflash, Topo) and technological spacecrafts (TRS, GGSE, LOFTI, Surcal, LCS, Timation, SERT).

- satellites for NASA (Alouette, Explorer 31, Echo 2, Pageos, OGO, Nimbus)

Thor Agena launches [chart 4]

#	Launch id	Payload	Launch date	Type	Status (orbit in perigee x apogee x inc. x period)
1	59002	Discoverer-1	28 Feb 1959	T AA	163 x 968 x 89.7 x 96
2	59003	Discoverer-2	13 Apr 1959	T AA	239 x 346 x 89.9 x 90.4
3	n/a	Discoverer-3	03 Jun 1959	T AA	Failure
4	n/a	Discoverer-4	25 Jun 1959	T AA	Failure
5	59005	Discoverer-5	13 Aug 1959	T AA	217 x 739 x 80 x 94.2
6	59006	Discoverer-6	19 Aug 1959	T AA	212 x 848 x 84 x 95.3
7	59010	Discoverer-7	07 Nov 1959	T AA	159 x 847 x 81.6 x 94.7
8	59011	Discoverer-8	20 Nov 1959	T AA	187 x 1679 x 80.7 x 103.7
9	n/a	Discoverer-9	04 Feb 1960	T AA	Failure
10	n/a	Discoverer-10	19 Feb 1960	T AA	Failure
11	60004	Discoverer-11	15 Apr 1960	T AA	170 x 589 x 80.1 x 92.2
12	n/a	Discoverer-12	29 Jun 1960	T AA	Failure
13	60008	Discoverer-13	10 Aug 1960	T AA	259 x 701 x 82.9 x 94
14	60010	KH 1-1 (D 14)	18 Aug 1960	T AA	186 x 805 x 79.7 x 94.6
15	60012	KH 1-2 (D 15)	13 Sep 1960	T AA	209 x 724 x 80.9 x 94.2
16	n/a	KH 2-1 (D 16)	26 Oct 1960	T AB	Failure
17	60015	Discoverer-17	12 Nov 1960	T AB	187 x 991 x 81.7 x 96.5
18	60018	KH 2-#? (D 19)	07 Dec 1960	T AB	233 x 661 x 81.5 x 93.7
19	60019	Discoverer-19	20 Dec 1960	T AB	206 x 520 x 83.4 x 93
20	61005	KH 5-1 (D 20)	17 Feb 1961	T AB	288 x 786 x 80.9 x 95.4
21	61006	Discoverer-21	18 Feb 1961	T AB	240 x 1069 x 80.7 x 97.9
22	n/a	Discoverer-22	30 Mar 1961	T AB	Failure
23	61011	Discoverer-23	08 Apr 1961	T AB	295 x 651 x 82.3 x 94.1
24	n/a	Discoverer-24	08 Jun 1961	T AB	Failure
25	61014	Discoverer-25	16 Jun 1961	T AB	222 x 409 x 82.1 x 90.9
26	61016	Discoverer-26	08 Jul 1961	T AB	235 x 809 x 82.9 x 95
27	n/a	Discoverer-27	21 Jul 1961	T AB	Failure
28	n/a	Discoverer-28	03 Aug 1961	T AB	Failure
29	61023	KH 3-1 (D 29)	30 Aug 1961	T AB	225 x 555 x 82.1 x 91.5
30	61024	Discoverer-30	12 Sep 1961	T AB	235 x 546 x 82.7 x 92.4
31	61026	Discoverer-31	17 Sep 1961	T AB	235 x 396 x 82.7 x 90.9
32	61027	Discoverer-32	13 Oct 1961	T AB	234 x 395 x 81.7 x 90.8
33	n/a	Discoverer-33	23 Oct 1961	T AB	Failure
34	61029	Discoverer-34	05 Nov 1961	T AB	227 x 1011 x 82.5 x 97.1
35	61030	Discoverer-35	15 Nov 1961	T AB	238 x 278 x 81.6 x 89.7
36	61034	A: Discoverer-36 B: Oscar 01	12 Dec 1961	T AB	338 x 450 x 81.2 x 91.8
37	n/a	Discoverer-37	13 Jan 1962	T AB	Failure
38	62004	KH (FTV 2301)	21 Feb 1962	T AB	167 x 374 x 82 x 90
39	62005	KH 4-1 (D 38)	27 Feb 1962	T AB	208 x 341 x 82.2 x 90
40	62011	KH (FTV 1154)	18 Apr 1962	T AB	199 x 297 x 73.5 x 90.9
41	62017	KH (FTV 1125)	29 Apr 1962	T AB	177 x 364 x 73.1 x 91.1
42	62018	KH 5-#? (FTV 1126)	15 May 1962	T AB	305 x 634 x 82.3 x 94
43	62021	KH (FTV 1128)	30 May 1962	T AB	199 x 319 x 74.1 x 89.7
44	62022	A: KH (FTV 1127) B: Oscar 02	02 Jun 1962	T AB	211 x 385 x 74.3 x 90.5
45	62024	ELINT 1#2 (FTV 2312)	18 Jun 1962	T AB	370 x 411 x 82.1 x 92.4
46	62026	KH (FTV 1129)	23 Jun 1962	T AB	213 x 293 x 75.1 x 89.6
47	62027	KH (FTV 1151)	28 Jun 1962	T AD	211 x 689 x 76 x 93.6
48	62031	KH (FTV 1130)	21 Jul 1962	T AB	208 x 381 x 70.9 x 90.4
49	62032	KH (FTV 1131)	28 Jul 1962	T AB	222 x 293 x 71.1 x 90.6
50	62034	KH (FTV 1152)	02 Aug 1962	T AD	204 x 418 x 82.2 x 90.8
51	62042	KH (FTV 1153)	29 Aug 1962	T AD	187 x 400 x 65.2 x 90.4
52	62044	KH 5-#? (FTV 1132)	01 Sep 1962	T AB	333 x 637 x 82.8 x 94.4
53	62046	KH (FTV 1133) + TRS-1	17 Sep 1962	T AB	204 x 668 x 81.8 x 93.3
54	62049	Alouette 1	29 Sep 1962	T AB
55	62050	KH (FTV 1154)	29 Sep 1962	T AD	203 x 376 x 65.4 x 90.3
56	62053	KH (FTV 1134)	09 Oct 1962	T AB	213 x 427 x 82 x 91
57	62058	Starad (FTV 1401)	26 Oct 1962	T AD	198 x 5570 x 71.4 x 147.9
58	62063	KH (FTV 1136)	05 Nov 1962	T AB	208 x 409 x 75 x 90.7
59	62065	KH (FTV 1135)	24 Nov 1962	T AB	204 x 337 x 65.1 x 89.9
60	62066	KH (FTV 1155)	04 Dec 1962	T AD	194 x 273 x 65.1 x 89.2
61	62067	A: Black Sphere B: Injun 3 C: Surcal 1 D: Surcal 1A E: Calsphere 1A	13 Dec 1962	T AD	235 x 2785 x 70.4 x 116.3
62	62069	KH (FTV 1156)	14 Dec 1962	T AD	199 x 392 x 71 x 90.5
63	63002	KH (FTV 1157)	07 Jan 1963	T AD	205 x 399 x 82.2 x 90.5
64	63003	ELINT 2#1 (FTV 2313)	16 Jan 1963	T AD	459 x 533 x 81.9 x 94.7
65	n/a	KH	28 Feb 1963	TAT AD	Failure
66	n/a	KH 6-1	18 Mar 1963	TAT AD	Failure
67	63007	KH (FTV 1660)	01 Apr 1963	T AD	201 x 408 x 75.4 x 90.7
68	n/a	KH	26 Apr 1963	T AD	Failure
69	63016	KH 6-2 (FTV 1110)	18 May 1963	TAT AD	153 x 497 x 74.5 x 91.1
70	63019	KH	13 Jun 1963	TAT AD	192 x 419 x 81.9 x 90.7
71	63021	B: LOFTI 2A C: Solrad 06A D: Radose 112 E: FTV 1292 F: Surcal 1B	15 Jun 1963	T AD	185 x 890 x 69.9 x 93
72	63025	KH + HitchHiker-1	27 Jun 1963	TAT AD	196 x 396 x 81.6 x 90.5
73	63027	ELINT 1#4	29 Jun 1963	TAT AB	484 x 536 x 82.3 x 94.8
74	63029	KH	18 Jul 1963	T AD	194 x 387 x 82.9 x 90.4
75	63032	KH 6-3 (last one)	31 Jul 1963	TAT AD	157 x 411 x 75 x 90.4
76	63034	KH 4A-1	24 Aug 1963	TAT AD	225 x 322 x 75 x 89.4
77	63035	KH + Ferret	29 Aug 1963	T AD	292 x 324 x 81.9 x 90.8
78	63037	KH	24 Sep 1963	TAT AD	161 x 441 x 74.9 x 90.6
79	63042	KH + Ferret	29 Oct 1963	TAT AD	279 x 345 x 89.9 x 90.8
80	n/a	KH	09 Nov 1963	T AD	Failure
81	63048	KH	27 Nov 1963	T AD	175 x 386 x 70 x 90.2
82	63055	KH 4-#? (last one)	21 Dec 1963	TAT AD	176 x 355 x 64.9 x 90
83	64001	B: GGSE 1 C: Secor 01B D: Solrad 07A	11 Jan 1964	T AD	905 x 935 x 69.9 x 103.5
84	64002	OPS 3367 A & B	19 Jan 1964	T AD	810 x 825 x 99.1 x 101.3
85	64004	Echo 2	25 Jan 1964	T AB
86	64008	KH 4A-3 (OPS 3444)	15 Feb 1964	TAT AD	179 x 444 x 75 x 90.9
87	64011	ELINT 2#2 (OPS 3722)	28 Feb 1964	TAT AD	479 x 520 x 82 x 94.7
88	n/a	KH	24 Mar 1964	TAT AD	Failure
89	64022	KH (OPS 2921)	27 Apr 1964	TAT AD	178 x 446 x 79.9 x 90.8
90	64026 or 027	KH	05 Jun 1964	TAT AD	149 x 429 x 80 x 90.3
91	64030	Starflash-1A	13 Jun 1964	T AD	350 x 364 x 115 x 91.7
92	64031	OPS 4467 A & B (2)	18 Jun 1964	T AD	828 x 842 x 99.8 x 101.6
93	64032	KH (OPS 3754)	19 Jun 1964	TAT AD	176 x 462 x 85 x 90.9
94	64035	ELINT 2#3 (OPS 3395)	03 Jul 1964	TAT AD	501 x 529 x 82.1 x 94.9
95	64037	KH (OPS 3491)	10 Jul 1964	TAT AD	180 x 461 x 85 x 91
96	64043	KH 5-12 (last one, OPS 3042)	05 Aug 1964	TAT AD	182 x 436 x 80 x 90.7
97	64048	Starflash-1B (OPS 2739)	21 Aug 1964	T AD	349 x 363 x 115 x 91.6
98	64052	Nimbus 1	28 Aug 1964	T AB
99	64056	KH 4A-#? (OPS 3497)	14 Sep 1964	TAT AD	238 x 466 x 85 x 90.9
100	64061	KH 4A-#? (OPS 3333)	05 Oct 1964	TAT AD	182 x 440 x 78 x 90.7
101	64067	KH 4A-#? (OPS 3559)	17 Oct 1964	TAT AD	189 x 416 x 75 x 90.6
102	64071	KH 4A-#? (OPS 5434)	02 Nov 1964	TAT AD	180 x 448 x 79.9 x 90.7
103	64072	ELINT 2#4 (OPS 3062)	04 Nov 1964	TAT AD	512 x 526 x 82 x 95.1
104	64075	KH 4A-#? (OPS 3360)	18 Nov 1964	TAT AD	180 x 339 x 70 x 89.7
105	64085	KH 4A-#? (OPS 3358)	19 Dec 1964	TAT AD	183 x 410 x 75 x 90.5
106	64087	KH 4A-#? (OPS 3762)	21 Dec 1964	TAT AD	238 x 264 x 70.1 x 89.5
107	65002	KH 4A-#? (OPS 3928)	15 Jan 1965	TAT AD	180 x 420 x 75 x 90.5
108	65013	KH 4A-#? (OPS 4782)	25 Feb 1965	TAT AD	177 x 377 x 75.1 x 90.1
109	65016	A: Solrad 06B B: GGSE 2 C: GGSE 3 D: Solrad 07B E: Secor 03 F: Oscar 03 G: Surcal 2 H: Porcupine 1 (Dodecapole 1)	09 Mar 1965	T AD
110	65026	KH 4A-#? (OPS 4803)	25 Mar 1965	TAT AD	186 x 265 x 96.1 x 89.1
111	65033	KH 4A-#? (OPS 5023)	29 Apr 1965	TAT AD	178 x 473 x 85 x 91
112	65037	KH 4A-#? (OPS 8431)	18 May 1965	TAT AD	198 x 331 x 75 x 89.7
113	65045	KH 4A-#? (OPS 8425)	09 Jun 1965	TAT AD	176 x 362 x 75.1 x 89.9
114	65055	ELINT 2#5 (OPS 8411)	17 Jul 1965	TAT AD	471 x 512 x 70.2 x 94.5
115	65057	KH 4A-#? (OPS 5543)	19 Jul 1965	TAT AD	182 x 464 x 85.1 x 91
116	65067	KH 4A-#? (OPS 7208)	17 Aug 1965	TAT AD	180 x 407 x 70 x 90.4
117	n/a	Starrad 2	02 Sep 1965	TAT AD	Failure
118	65074	KH 4A-#? (OPS 7221)	22 Sep 1965	TAT AD	191 x 364 x 80 x 90
119	65079	KH 4A-#? (OPS 5325)	05 Oct 1965	TAT AD	203 x 323 x 75 x 89.8
120	65081	OGO 2	14 Oct 1965	TAT AD	415 x 1517 x 87.4 x 104.4
121	65086	KH 4A-#? (OPS 2155)	28 Oct 1965	TAT AD	176 x 430 x 75 x 90.5
122	65098	Alouette 2 Explorer 31	29 Nov 1965	T AB
123	65102	KH 4A-#? (OPS 7249)	09 Dec 1965	TAT AD	183 x 437 x 80 x 90.7
124	65110	KH 4A-#? (OPS 4639)	24 Dec 1965	TAT AD	178 x 446 x 80 x 90.8
125	66007	KH 4A-#? (OPS 7291)	02 Feb 1966	TAT AD	185 x 425 x 75.1 x 90.6
126	66009	ELINT 2#6 (OPS 1439)	09 Feb 1966	TAT AD	508 x 512 x 82.1 x 94.8
127	66018	KH 4A-#? (OPS 3488)	09 Mar 1966	TAT AD	178 x 432 x 75 x 90.6
128	66029	KH 4A-#? (OPS 1612)	07 Apr 1966	TAT AD	193 x 312 x 75.41 x 89.6
129	n/a	KH 4A-#?	03 May 1966	TAT AD	Failure
130	66040	Nimbus 2	15 May 1966	TAT AB	or was it a TAT AB ?
131	66042	KH 4A-#? (OPS 1778)	24 May 1966	TAT AD	179 x 271 x 66 x 89
132	66055	KH 4A-#? (OPS 1599)	21 Jun 1966	TAT AD	194 x 367 x 80.1 x 90.2
133	66056	Pageos	24 Jun 1966	TAT AD
134	66072	KH 4A-#? (OPS 1545)	09 Aug 1966	LTTAT AD	194 x 287 x 100.1 x 89.4
135	66085	KH 4A-#? (OPS 1703)	20 Sep 1966	TAT AD	188 x 442 x 85.1 x 90.9
136	66102	KH 4A-#? (OPS 1866)	08 Nov 1966	TAT AD	172 x 318 x 100.1 x 89.4
137	66118	ELINT 2#7 (OPS 1584)	29 Dec 1966	TAT AD	486 x 496 x 75 x 94.4
138	67002	KH 4A-#? (OPS 1664)	14 Jan 1967	TAT AD	180 x 380 x 80.1 x 90.1
139	67015	KH 4A-#? (OPS 4750)	22 Feb 1967	TAT AD	180 x 380 x 80 x 90.1
140	67029	KH 4A-#? (OPS 4779)	30 Mar 1967	TAT AD	167 x 326 x 85 x 89.5
141	67043	KH 4A-#? + Ferret (OPS 4696 + 1967)	09 May 1967	LTTAT AD	200 x 777 x 85.1 x 94.4
142	67053	A: OPS 5712 C: GGSE 4 D: GGSE 5 E: Timation 1 F: Surcal 159 J: Surcal 150B	31 May 1967	T AD	914 x 928 x 70 x 103.5
143	67062	KH 4A-#? + Ferret (OPS 3559 + 1873)	16 Jun 1967	LTTAT AD	181 x 367 x 80 x 90
144	67071	ELINT 2#8 (OPS 1879)	25 Jul 1967	TAT AD	390 x 582 x 75.1 x 94.3
145	67073	OGO 4	28 Jul 1967	TAT AD	411 x 903 x 86 x 97.9
146	67076	KH 4A-49 (last one, OPS 4827)	07 Aug 1967	LTTAT AD	174 x 346 x 79.9 x 89.7
147	67087	KH 4B-1 (OPS 5089)	15 Sep 1967	LTTAT AD	150 x 389 x 80.1 x 89.9
148	67109	KH 4B-2 + Ferret (OPS 0562 + 1587)	02 Nov 1967	LTTAT AD	183 x 410 x 81.5 x 90.5
149	67122	KH 4B-3 (OPS 1001)	09 Dec 1967	LTTAT AD	158 x 237 x 81.7 x 88.5
150	68004	ELINT 2#9 (OPS 1965)	17 Jan 1968	TAT AD	450 x 576 x 75.2 x 94.5
151	68008	KH 4B-4 + Ferret (OPS 2243 + 6236)	24 Jan 1968	LTTAT AD	176 x 430 x 81.5 x 90.6
152	68020	KH 4B-5 + Ferret (OPS 4849 + 7076)	14 Mar 1968	LTTAT AD	178 x 391 x 83 x 90.2
153	68039	KH 4B-6 (OPS 1419)	01 May 1968	LTTAT AD	164 x 243 x 83.1 x 88.6
154	n/a	Nimbus 3A Secor-10	18 May 1968	LTTAT AD	Failure
155	68052	KH 4B-7 + Ferret (OPS 5343 + 5259)	20 Jun 1968	LTTAT AD	193 x 326 x 85 x 89.7
156	68065	KH 4B-8 (OPS 5955)	07 Aug 1968	LTTAT AD	152 x 257 x 82.1 x 88.6
157	68078	KH 4B-9 + Ferret (OPS 0165 + 8595)	18 Sep 1968	LTTAT AD	167 x 343 x 83 x 90.1
158	68086	ELINT 2#10 (OPS 0964)	05 Oct 1968	T AD	483 x 511 x 75 x 94.6
159	68098	KH 4B-10 (OPS 1315)	03 Nov 1968	LTTAT AD	150 x 288 x 82.2 x 88.9
160	68112	KH 4B-11 + Ferret (OPS 4740 + 7684)	12 Dec 1968	LTTAT AD	169 x 248 x 81 x 88.7
161	69010	KH 4B-12 + Ferret (OPS 3890 + 2644)	05 Feb 1969	LTTAT AD	178 x 239 x 81.5 x 88.7
162	69026	KH 4B-13 + Ferret (OPS 3722 + 2285)	19 Mar 1969	LTTAT AD	179 x 241 x 83 x 88.7
163	69037	Nimbus 3 Secor 13	14 Apr 1969	LTTAT AD
164	69041	KH 4B-14 + Ferret (OPS 1101 + 1721)	02 May 1969	LTTAT AD	179 x 326 x 66 x 89.5
165	69051	OGO 6	05 Jun 1969	LTTAT AD
166	69063	KH 4B-15 (OPS 3654)	24 Jul 1969	LTTAT AD	187 x 211 x 75 x 88.5
167	69065	ELINT 3#1 (OPS 8285)	31 Jul 1969	LTTAT AD	153 x 574 x 75 x 91.5
168	69079	KH 4B-16 + Ferret (OPS 3531 + 4710)	22 Sep 1969	LTTAT AD	180 x 250 x 85 x 88.8
169		OV-5 + Secor + LCS+?	30 Sep 1969	TAT AD	450 x 480 x 70 x 93.9
170	69105	KH 4B-17 (OPS 6617)	04 Dec 1969	LTTAT AD	159 x 251 x 81.5 x 88.6
171	70009	SERT-2	04 Feb 1970	LTTAT AD	995 x 1006 x 99.1 x 105
172	70016	KH 4B-18 + Ferret (OPS 0440 + 3402)	04 Mar 1970	LTTAT AD	159 x 167 x 88 x 87.7
173	70025	Nimbus 4 Topo-1 (SECOR)	08 Apr 1970	LTTAT AD	1093 x 1107 x 99.8 x 107
174	70040	KH 4B-18 + Ferret (OPS 4720 + 8520)	20 May 1970	LTTAT AD	162 x 246 x 83 x 88.6
175	70054	KH 4B-19 (OPS 4324)	23 Jul 1970	LTTAT AD	158 x 398 x 60 x 90
176	70066	ELINT 3#2 (OPS 8329)	26 Aug 1970	LTTAT AD	484 x 504 x 75 x 94.5
177	70098	KH 4B-20 + Ferret (OPS 4992 + 6829)	18 Nov 1970	LTTAT AD	185 x 232 x 83 x 88.7
178	71012	KH 4B-21 (OPS 5268)	17 Feb 1971	LTTAT AD	Failure
179	71022	KH 4B-22 (OPS 5300)	24 Mar 1971	LTTAT AD	158 x 246 x 81.5 x 88.6
180	71060	ELINT 3#3 (OPS 8373)	16 Jul 1971	LTTAT AD	488 x 507 x 75 x 94.6
181	71076	KH 4B-23 + Ferret (OPS 5454 + 7681)	10 Sep 1971	LTTAT AD	156 x 244 x 74.9 x 88.5
182	71089	STP-1 (Astex 1)	17 Oct 1971	LTTAT AD	772 x 803 x 92.7 x 100.6
183	71110	NOSS (experimental) (OPS 7898)	14 Dec 1971	LTTAT AD	984 x 998 x 70 x 104.9
184	72032	KH 4B-24 (OPS 5640)	19 Apr 1972	LTTAT AD	154 x 277 x 81.5 x 88.8
185	72039	KH 4B-25 (OPS 6371)	25 May 1972	LTTAT AD	158 x 305 x 96.3 x 89.2

Notes: in the type column, AA, AB & AD stand for Agena A, B et D; T stands for Thor, TAT for Thrust Augmented Thor and LTTAT for Long Tank Thrust Augmented Thor. All launches from Vandenberg.


 Thor Delta

Jean-Jacques Serra

Gunter Krebs (listing)

At the end of 1958, not long after NASA was founded, the necessity of a new civilian launcher arose. This vehicle was to be available quickly until the arrival of the Atlas and Centaur. The basic stage could only be Thor associated with one of the 3 top stages available: Able, Ablestar and Agena. Refering to the fourth letter of the Greek alphabet NASA named this new stage Delta in January 1959. Three months later the construction was granted to Douglas Aircraft (a dozen rockets were ordered) and the naming Thor Delta (or simply Delta) was adopted.

The original Delta was almost identical to Thor Able: first stage was Thor, and the second and third stage was inherited from Vanguard. The improvments were in the field of inertial guiding and active piloting during the ballistic phase between shutdown of the second stage and ignition of the third stage. This first version was 27.8 m high and weighed 51 tons; it could put 45 kg in LEO.

Its first launch on 13 May 1960 ended in a failure; the third stage didn't work. But the 12 August the second Delta was successful in orbiting Echo 1; this was the first of 22 successes. NASA went on using such launchers because of their reliability and their low cost and because of the improvements made by Douglas then McDonnell Douglas.

The A version (1962) resulted of the use of the MB3-3 motor; the B version (1962) of the lengthening of the second stage; the C version (1963) had a new third stage; the D version (1964) had Castor boosters added to the first stage. The TAD (Thrust Augmented Delta) could place 450 kg on a 800 km orbit.

The second stage was replaced in the E version (1965) resulting in the TAID (Thrust Augmented Improved Delta). The diameter of the second stage changed from 0.92 m to 1.43 m. This tripled the combustion time. The LTTAD (Long Tank Thrust Augmented Delta) appeared in the M version in 1968. the M-6 version of 1969 featured 6 Castor boosters; 3 ignited at takeoff and the others burned after the first ones shutdowned. Then not 6 but 9 boosters were included which enabled Delta to deliver 350 kg in GEO and 650 kg in a 550 km circular orbit (in 2-stage configuration).

"Straight 8" appeared in the early 70ies; this Delta version had a constant diameter: 2.44 m (8 ft). The version naming changed at the same time to become a 4-digit number: the two first digits specify the type of the first stage and the number of strap-on boosters. The two last digits refer to the type of the second and the third stage.

The 2910 version featured a Rocketdyne RS-27 first stage motor burning during 225 seconds and 9 Castor-2 boosters. The second stage was made from an Aerojet AJ10-118F motor (aerozin 50 & N204) delivering 4.3 t thrust during 320 seconds or a TRW TR-201 motor derived from the Lem descent motor using the same propellants. The 2-stage 2910 Delta could deliver 2 tons in orbit. The 3-stage 2914 version launched for the first time in 1972 featured a Thiokol TE 364-4 third stage motor providing 6.5 tons thrust during 44 seconds; it could launch 720 kg payloads in geosynchronous orbit.

The 2900 series was to be the last Delta series but as the Shuttle wasn't operational before 1980 NASA ordered the development of a new series for heavier payloads.

The 3914 Delta appeared in 1975. This version had its Castor-2s replaced by Castor-4s of 1 m diameter and 10 m high providing each 42 tons thrust during 56 seconds. The GEO capacity reached 930 kg. In 1980 as the third stage was replaced by a PAM-D (Payload Assist Module / Delta) equipped with a Thiokol Star 48 engine capable of 8.6 tons thrust during 85 seconds; Delta 3910 PAM peformance reached 1090 kg in GEO. In 1982 the second stage was replaced by a larger version (+30% propellant) with an Aerojet AJ10-118K (borrowed from Titan-3's Transtage) providing 4.35 tons thrust during 430 seconds. This Delta 3920 PAM of 35.5 m high could launch 1250 kg in GEO.

In 1984 NASA transfered Delta to a private company: Transpace Carrier Inc. At the end on the year it was believed that the launcher would be abandonned and replaced by the Shuttle. But after Challenger's accident in 1986 the launcher reappeared.

In 1987 the improved Delta was selected by the USAF as Medium Launch Vehicle (MLV) to place in orbit the second generation of Navstar satellites. The new launched was named Delta-2 and was designed in two stages: first the 6920 series then the 7920 series. The 6925 version was derived from Delta 3920 PAM by replacing the boosters by Castor-4As and lengthening the first stage of 3.65 m, extending the burn duration to 265 seconds. The diameter of the bulb cap was upped to 2.83 m. The launcher which first flew in 1989 was 39.6 m high, weighed 215 tons and could place 1400 kg in GEO.

The latest version is model 7925 which first launch occured in 1991. Its first stage is equipped with a RS-27 motor which nozzle was lengthened (12:1 instead of 8:1). The Thiokol boosters were replaced by Hercules GEM (Graphite Epoxy Motors) with weight reduced structure. Those boosters are 12 m long, weigh over 12.7 tons and provide 4.8 tons thrust. Delta 7925 weighs 225 tons and can place 1610 kg in GEO.

Delta in its different Delta-1 configurations launched numerous satellites on various orbits especially scientific satellites:

- with low perigee (ADE)

- with high apogee (IMP, ISEE 1 & ISEE 2, Exosat)

- in lunar orbit (IMP-F, RAE-B)

- to the Solar-Earth Lagrange point (ISEE-3)

- and interplanetary probes (Pioneer, ICE former-ISEE-3)

Among the scientific mission satellites some were launched:

- with collaboration (ISEE, IUE, AMPTE)

- for foreign states (Ariel, Isis, IRAS)

- or for international organizations (Heos, TD 1A, ISEE 2, COS B, ESA-Geos 1, ESA-Geos 2, Exosat)

Application missions were aimed at:

- meteorology (Tiros, Essa, Itos/NOAA, Nimbus, SMS, Goes)

- remote sensing (Landsat)

Especially for telecommunication satellites such as:

- American satellites (Telstar, Relay, Syncom, Westar, Satcom, SBS, Galaxy)

- International satellites (Intelsat, NATO)

- or foreign satellites (Skynet, Anik, Symphonie, CTS, Palapa, OTS, Sirio, Insat...)

Delta-2 versions were initially developped for the Navstar-2 satellites... but is not limited to them:

- scientific satellites (Cobe, Rosat, EUVE, Geotail)

- telecommunication satellites (BSB, Satcom, NATO,...)

Thor Delta launches [chart 5]

#	Launch id	Payload	Launch date	Site	Type	Status (orbit in perigee x apogee x inc. x period)
1	n/a	Echo 1	13 May 1960	C	DM19	Failure
2	60009	Echo 1A	12 Aug 1960	C	DM19
3	60016	Tiros 02	23 Nov 1960	C	DM19
4	61010	Explorer 10	25 Mar 1961	C	DM19
5	61017	Tiros 03	12 Jul 1961	C	DM19
6	61020	Explorer 12	15 Aug 1961	C	DM19
7	62002	Tiros 04	08 Feb 1962	C	DM19
8	62006	OSO 1	07 Mar 1962	C	DM19
9	62015	Ariel 1	26 Apr 1962	C	DM19
10	62025	Tiros 05	19 Jun 1962	C	DM19
11	62029	Telstar 1	10 Jul 1962	C	DM19
12	62047	Tiros 06	18 Sep 1962	C	DM19
13	62051	Explorer 14	02 Oct 1962	C	A
14	62059	Explorer 15	27 Oct 1962	C	DM19
15	62068	Relay 1	13 Dec 1962	C	B
16	63004	Syncom 1	14 Feb 1963	C	B
17	63009	Explorer 17	03 Apr 1963	C	B
18	63013	Telstar 2	07 May 1963	C	B
19	63024	Tiros 07	19 Jun 1963	C	B
20	63031	Syncom 2	26 Jul 1963	C	B
21	63046	Explorer 18	27 Nov 1963	C	C
22	63054	Tiros 08	21 Dec 1963	C	B
23	64003	Relay 2	21 Jan 1964	C	B
24	n/a	Explorer (BE A)	19 Mar 1964	C	B	Failure
25	64047	Syncom 3	19 Aug 1964	C	D
26	64060	Explorer 21	04 Oct 1964	C	C
27	64086	Explorer 26	21 Dec 1964	C	C
28	65004	Tiros 09	22 Jan 1965	C	C
29	65007	OSO 2	03 Feb 1965	C	C
30	65028	Intelsat 101	06 Apr 1965	C	D
31	65042	Explorer 28	29 May 1965	C	C
32	65051	Tiros 10	02 Jul 1965	C	C
33	n/a	OSO C	25 Aug 1965	C	C	Failure
34	65089	Explorer 29	06 Nov 1965	C	E
35	65105	Pioneer-6	16 Dec 1965	C	E	Interplanetary probe
36	66008	Essa 1	03 Feb 1966	C	C
37	66016	Essa 2	28 Feb 1966	C	E
38	66044	Explorer 32	25 May 1966	C	C1
39	66058	Explorer 33	01 Jul 1966	C	E1	30532 x 494230 x 29 x 19488
40	66075	Pioneer-7	17 Aug 1966	C	E1	Interplanetary probe
41	66087	Essa 3	02 Oct 1966	V	E
42	66096	Intelsat 201	26 Oct 1966	C	E1	Partial failure
43	66114	Biosat-1	14 Dec 1966	C	G	295 x 309 x 33.5 x 90.4
44	67001	Intelsat 202	11 Jan 1967	C	E1
45	67006	Essa 4	26 Jan 1967	V	E
46	67020	OSO 3	08 Mar 1967	C	C
47	67026	Intelsat 203	23 Mar 1967	C	E1
48	67036	Essa 5	20 Apr 1967	V	E
49	67051	Explorer 34	24 May 1967	V	E1
50	67070	Explorer 35 (IMP)	19 Jul 1967	C	E1	Lunar orbit
51	67083	Biosat-2	07 Sep 1967	C	G	286 x 313 x 33.5 x 90.4
52	67094	Intelsat 204	28 Sep 1967	C	E1
53	67100	OSO 4	18 Oct 1967	C	E1
54	67114	Essa 6	10 Nov 1967	V	C1
55	67123	Pioneer-8 TATS 1 (TETR 1)	13 Dec 1967	C	E1	Interplanetary probe
56	68002	Explorer 36	11 Jan 1968	V	E1
57	68055	Explorer 38	04 Jul 1968	V	J
58	68069	Essa 7	16 Aug 1968	V	N
59	n/a	Intelsat 301	18 Sep 1968	C	M	Failure
60	68100	Pioneer-9 TETR 2	08 Nov 1968	C	E1	Interplanetary probe
61	68109	Heos 1	05 Dec 1968	C	E1
62	68114	Essa 8	15 Dec 1968	V	N
63	68116	Intelsat 302	19 Dec 1968	C	M
64	69006	OSO 5	22 Jan 1969	C	C1
65	69009	Isis 1	30 Jan 1969	V	E1
66	69011	Intelsat 303	06 Feb 1969	C	M
67	69016	Essa 9	26 Feb 1969	C	E1
68	69045	Intelsat 304	22 May 1969	C	M
69	69053	Explorer 41	21 Jun 1969	V	E1
70	69056	Biosat-3	29 Jun 1969	C	N
71	69064	Intelsat 305	25 Jul 1969	C	N	Partial failure
72	69068	OSO 6	09 Aug 1969	C	N
73	n/a	Pioneer-10A	28 Sep 1969	C	L	Failure
74	69101	Skynet 1A	22 Nov 1969	C	M
75	70003	Intelsat 306	15 Jan 1970	C	M
76	70008	Itos Oscar 05	23 Jan 1970	V	N6
77	70021	Nato 1	20 Mar 1970	C	M
78	70032	Intelsat 307	23 Apr 1970	C	M
79	70055	Intelsat 308	23 Jul 1970	C	M
80	70062	Skynet 1B	19 Aug 1970	C	M
81	70106	NOAA 01 CEP 1	11 Dec 1970	V	N6	CEP 1 was attached to the 2nd stage
82	71009	Nato 2	03 Feb 1971	C	L
83	71019	Explorer 43	13 Mar 1971	C	M6
84	71024	Isis 2	01 Apr 1971	V	E1
85	71083	OSO 7	29 Sep 1971	C	N
86	71091	ITOS-3/NOAA	21 Oct 1971	V	N6	payload exploded?
87	72005	Heos 2	31 Jan 1972	V	L
88	72014	TD-1A	12 Mar 1972	V	N
89	72058	Landsat 1	23 Jul 1972	V	900
90	72073	Explorer 47	23 Sep 1972	C	1604
91	72082	NOAA 02	15 Oct 1972	V	300
92	72090	Anik A1	10 Nov 1972	C	1914
93	72097	Nimbus 5	11 Dec 1972	V	900
94	73023	Anik A2	20 Apr 1973	C	1914
95	73039	Explorer 49 (RAE B)	10 Jun 1973	C	1913	Lunar orbit
96	n/a	Itos E	16 Jul 1973	V	300	Failure
97	73078	Explorer 50	26 Oct 1973	C	1604
98	73086	NOAA 03	06 Nov 1973	V	300
99	73101	Explorer 51	16 Dec 1973	V	900
100	74002	Skynet 2A	19 Jan 1974	C	2913	Partial failure
101	74022	Westar 1	13 Apr 1974	C	2914
102	74033	SMS 1	17 May 1974	C	2914
103	74075	Westar 2	10 Oct 1974	C	2914
104	74089	NOAA 04 Oscar 07 Intasat	15 Nov 1974 at 17:11 UT	V	2310
105	74094	Skynet 2B	23 Nov 1974	C	2913
106	74101	Symphonie 1	19 Dec 1974	C	2914
107	75004	Landsat 2	22 Jan 1975	V	2910
108	75011	SMS 2	06 Feb 1975	C	2914
109	75027	Geos 3	09 Apr 1975	V	2310
110	75038	Anik A3	07 May 1975	C	2914
111	75052	Nimbus 6	12 Jun 1975	V	2910
112	75057	OSO 8	21 Jun 1975	C	2913
113	75072	Cos B	09 Aug 1975	V	2914
114	75077	Symphonie 2	27 Aug 1975	C	2914
115	75096	Explorer 54	06 Oct 1975	V	2910
116	75100	Goes 1	16 Oct 1975	C	2914
117	75107	Explorer 55	20 Nov 1975	C	2910
118	75117	Satcom 1	13 Dec 1975	C	3914
119	76004	CTS	17 Jan 1976	C	2914
120	76017	Marisat 1	19 Feb 1976	C	2914
121	76029	Satcom 2	26 Mar 1976	C	3914
122	76035	Nato 3A	22 Apr 1976	C	2914
123	76039	Lageos 1	04 May 1976	V	2913
124	76053	Marisat 2	10 Jun 1976	C	2914
125	76066	Palapa A1	08 Jul 1976	C	2914
126	76077	NOAA 05	29 Jul 1976	V	2310
127	76101	Marisat 3	14 Oct 1976	C	2914
128	77005	Nato 3B	28 Jan 1977	C	2914
129	77018	Palapa A2	10 Mar 1977	C	2914
130	77029	ESA-Geos 1	20 Apr 1977	C	2914
131	77048	Goes 2	16 Jun 1977	C	2914
132	77065	GMS 1	14 Jul 1977	C	2914
133	77080	Sirio 1	25 Aug 1977	C	2913
134	n/a	OTS 1	13 Sep 1977	C	3914	Failure
135	77102	ISEE 1 ISEE 2	22 Oct 1977	C	2914
136	77108	Meteosat 1	23 Nov 1977	C	2914
137	77118	Sakura 1	15 Dec 1977	C	2914
138	78012	IUE	26 Jan 1978	C	2914
139	78026	Landsat 3 Oscar 08 PIX 1	5 Mar 1978	V	2910	PIX 1 was attached to the 2nd stage
140	78039	Yuri 1	07 Apr 1978	C	2914
141	78044	OTS 2	11 May 1978	C	3914
142	78062	Goes 3	16 Jun 1978	C	2914
143	78071	ESA-Geos 2	14 Jul 1978	C	2914
144	78079	ISEE-3	11 Aug 1978	C	2914	To the Lagrange point and then became ICE
145	78098	Nimbus 7 Cameo	24 Oct 1978	V	2910	Cameo was attached to the 2nd stage
146	78106	Nato 3C	19 Nov 1978	C	2914
147	78116	Anik B1 Drims	16 Dec 1978	C	3914	Drims was attached to the 2nd stage
148	79007	Scatha (P78 2)	30 Jan 1979	C	2914	27800 x 42300 x 8.3 x 1441
149	79072	Westar 3	10 Aug 1979	C	2914
150	79101	Satcom 3	07 Dec 1979	C	3914
151	80014	SMM	14 Feb 1980	C	3910
152	80074	Goes 4	09 Sep 1980	C	3914
153	80091	SBS 1	15 Nov 1980	C	3910/PAM
154	81049	Goes 5	22 May 1981	C	3914
155	81070	Dynamics Explorer 1 Dynamics Explorer 2	03 Aug 1981	V	3913	Partial failure
156	81096	SBS 2	24 Sep 1981	C	3910/PAM
157	81100	SME Uosat 1	06 Oct 1981	V	2310
158	81114	Satcom 3R	20 Nov 1981	C	3910/PAM
159	82004	Satcom 4	16 Jan 1982	C	3910/PAM
160	82014	Westar 4	26 Feb 1982	C	3910/PAM
161	82031	Insat 1A	10 Apr 1982	C	3910/PAM
162	82058	Westar 5	09 Jun 1982	C	3910/PAM
163	82072	Landsat 4	16 Jul 1982	V	3920
164	82082	Anik D1	26 Aug 1982	C	3920/PAM
165	82105	Aurora 1	28 Oct 1982	C	3924
166	83004	IRAS PIX 2	26 Jan 1983	V	3910	PIX 2 was attached to the 2nd stage
167	83030	Satcom 1R	11 Apr 1983	C	3924
168	83041	Goes 6	28 Apr 1983	C	3914
169	83051	Exosat	26 May 1983	V	3914
170	83065	Galaxy 1	28 Jun 1983	C	3920/PAM
171	83077	Telstar 301	28 Jul 1983	C	3920/PAM
172	83094	Satcom 2R	08 Sep 1983	C	3924
173	83098	Galaxy 2	22 Sep 1983	C	3920/PAM
174	84021	Landsat 5 Uosat 2	01 Mar 1984	V	3920
175	84088	AMPTE CCE AMPTE IRM AMPTE UKS	16 Aug 1984	C	3924
176	84101	Galaxy 3	21 Sep 1984	C	3920/PAM
177	84115	Nato 3D	14 Nov 1984	C	3914
178	n/a	Goes G	03 May 1986	C	3914	Failure
179	86069	USA 019 (SDIO)	05 Sep 1986	C	3920
180	87022	Goes 7	26 Feb 1987	C	3924
181	87029	Palapa B2P	20 Mar 1987	C	3920/PAM
182	88008	USA-30 (SDIO)	08 Feb 1988	C	3920	220 x 340 x 28.6 x 90
183	89013	GPS BII-01	14 Feb 1989	C	6925
184	89026	Delta Star	24 Mar 1989	C	3920
185	89044	GPS BII-02	10 Jun 1989	C	6925
186	89064	GPS BII-03	18 Aug 1989	C	6925
187	89067	BSB 1	27 Aug 1989	C	4925
188	89085	GPS BII-04	21 Oct 1989	C	6925
189	89089	Cobe	18 Nov 1989	V	5920
190	89097	GPS BII-05	11 Dec 1989	C	6925
191	90008	GPS BII-06	24 Jan 1990	C	6925
192	90015	USA 051 + 052 (LACE + RME; SDIO)	14 Feb 1990	C	6920-8	500 x 500 x 43.1
193	90025	GPS BII-07	26 Mar 1990	C	6925
194	90034	Palapa B2R	13 Apr 1990	C	6925-8
195	90049	Rosat	01 Jun 1990	C	6920-10
196	90051	Insat 1D	12 Jun 1990	C	4925
197	90068	GPS BII-08	02 Aug 1990	C	6925
198	90074	BSB 2	19 Aug 1990	C	6925
199	90088	GPS BII-09	01 Oct 1990	C	6925
200	90093	Inmarsat 2F1	30 Oct 1990	C	6925
201	90103	GPS BIIA-10	26 Nov 1990	C	7925
202	91001	Nato 4A	08 Jan 1991	C	7925
203	91018	Inmarsat 2F2	08 Mar 1991	C	6925
204	91028	ASC 2	13 Apr 1991	C	7925
205	91037	Aurora 2	29 May 1991	C	7925
206	91047	GPS BIIA-11 Losat-X	04 Jul 1991	C	7925
207	92009	GPS BIIA-12	23 Feb 1992	C	7925
208	92019	GPS BIIA-13	10 Apr 1992	C	7925
209	92027	Palapa B4	14 May 1992	C	7925-8
210	92031	EUVE	07 Jun 1992	C	6920-10
211	92039	GPS BIIA-14	07 Jul 1992	C	7925
212	92044	Geotail Duve	24 Jul 1992	C	6925	Duve was attached to the 2nd stage
213	92057	Satcom C4	31 Aug 1992	C	7925
214	92058	GPS BIIA-15	09 Sep 1992	C	7925
215	92066	DFS 3	12 Oct 1992	C	7925
216	92079	GPS BIIA-16	22 Nov 1992	C	7925
217	92089	GPS BIIA-17	18 Dec 1992	C	7925
218	93007	GPS BIIA-18	03 Feb 1993	C	7925
219	93017	GPS BIIA-19 Seds 1	30 Mar 1993	C 17A	7925	Seds 1 was tethered to 2nd stage
220	93032	GPS BIIA-20	13 May 1993	C	7925
221	93042	GPS BIIA-21 PMG	26 Jun 1993	C	7925	PMG was tethered to 2nd stage
222	93054	GPS BIIA-22	30 Aug 1993	C 17	7925
223	93068	GPS BIIA-23	26 Oct 1993	C 17	7925
224	93076	Nato 4B	08 Dec 1993	C	7925
225	94013	Galaxy 1R	19 Feb 1994	C 17	7925-8
226	94016	GPS BIIA-24 Seds 2	10 Mar 1994	C 17	7925	Seds 2 was tethered to 2nd stage
227	94071	Wind 1	01 Nov 1994	C 17B	7925-10
228	95041	Koreasat 1	05 Aug 1995	C 17B	7925	Partial failure: a booster failed to separate
229	95059	Radarsat Surfsat 1	04 Nov 1995 at 14:22 UT	V SLC2	7920-10	Surfsat is attached to Delta's second stage
230	95074	XTE	30 Dec 1995 at 13:48 UT	C 17A	7920-10
231	96003	Koreasat 2	14 Jan 1996 at 11:11 UT	C 17B	7925
232	96008	NEAR probe	17 Feb 1996 at 20:43 UT	C 17B	7925-8
233	96011	Polar	24 Feb 1996	V SLC2	7925-10	185 x 50494 km x 86°
234	96019	GPS BIIA-25	28 Mar 1996 at 00:21 UT	C 17A	7925	192 x 20269 km x 34.9°

Notes: in the launcher date & site column C stands for Cape Canaveral and V for Vandenberg.


Thor with solid top stage
 Thor with a solid fuel top stage

Jean-Jacques Serra

Gunter Krebs (listing)

The first top stage associated to Thor in 1965 was Altair, the former third stage of Vanguard. Boeing's Burner was also adapted to Thor; this is the only top stage with full control and guiding capacities. The Burner-I featured an Altair motor while the Burner-II was equipped with the TE364 (the Lunar probe Surveyor main engine retro-rocket providing a 4.5-ton thrust). The Burner-IIA was a two stage version which second stage provided 4 tons thrust.

Thor Altair and Thor Burner were mainly used for US military meteorological programs although they also launched technological satellites.

Thor with solid top stage launches [chart 6]

# and serial	Launch id	Payload	Launch date	Type	Status (orbit in perigee x apogee x inclination x period)
1, 224		DMSP B4A-01	19 Jan 1965	LV2D Burner1	471 x 822 x 98.8 x 97.7
2, 306		DMSP B4A-02	18 Mar 1965	LV2D Burner1	525 x 764 x 99.1 x 97.7
3, 282		DMSP B4A-03	20 May 1965	LV2D Burner1	567 x 953 x 98.7 x 100.1
4, 213		DMSP B4A-04	10 Sep 1965	LV2D Burner1	649 x 1054 x 98.7 x 101.9
5, 251		DMSP B4A-05	06 Jan 1966	LV2D Burner1	Failure: 2nd stage failed
6, 147		DMSP B4A-06	31 Mar 1966	LV2D Burner1	634 x 933 x 98.6 x 100.6
7, 167		DMSP B4A-07	16 Sep 1966	LV2D Burner2	705 x 891 x 98.5 x 100.9
8, 169		DMSP B4A-08	08 Feb 1967	LV2D Burner2	796 x 868 x 98.8 x 101.6
9, 171	67065	Secor 09 Aurora 1 (P67-1)	29 Jun 1967	LV2D Burner2
10, 266		DMSP B4A-09	23 Aug 1967	LV2D Burner2	834 x 892 x 99 x 102.2
11, 268		DMSP B4A-10	11 Oct 1967	LV2D Burner2	694 x 837 x 99.1 x 100.2
12, 277		DMSP B5A-1	23 May 1968	LV2D Burner2	817 x 904 x 98.9 x 102.2
13, 173		DMSP B5A-2	23 Oct 1968	LV2D Burner2	797 x 855 x 99 x 101.4
14, 279		DMSP B5A-3	23 Jul 1969	LV2D Burner2	791 x 863 x 99 x 101
15, 287		DMSP B5A-4	11 Feb 1970	LV2D Burner2	764 x 974 x 98.7 x 101.6
16, 288		DMSP B5A-5	03 Sep 1970	LV2D Burner2	764 x 874 x 98.7 x 101.3
17, 249		DMSP B5A-6 Calsphere 3, 4, 5	17 Feb 1971	LV2D Burner2	767 x 833 x 98.8 x 100.9
18, 210		SESP-1 (P70-1)	08 Jun 1971	LV2D Burner2	545 x 581 x 90.2 x 95.9
19, 159		DMSP B5B-1	14 Oct 1971	LV2D Burner2A	796 x 877 x 99 x 101.7
20, 153		DMSP B5B-2	24 Mar 1972	LV2D Burner2A	803 x 885 x 98.8 x 101.8
21, 294		DMSP B5B-3	09 Nov 1972	LV2D Burner2A	813 x 872 x 98.6 x 101.8
22, 291		DMSP B5B-4	17 Aug 1973	LV2D Burner2A	811 x 852 x 98.9 x 101.6
23, 207		DMSP B5B-5	16 Mar 1974	LV2D Burner2A	780 x 876 x 98.9 x 101.5
24, 275		DMSP B5B-6	09 Aug 1974	LV2D Burner2A	808 x 870 x 98.8 x 101.7
25, 197		DMSP B5C-1	24 May 1975	LV2D Burner2A	830 x 904 x 98.9 x 102.2
26, 182		DMSP B5C-2	21 Feb 1976	LV2D Burner2A	Partial failure: Thor failed, wrong orbit attained
27, 172		DMSP B5D1-1	11 Sep 1976	LV2F S3B S37B-ISS	820 x 845 x 99
28, 183		DMSP B5D1-2	05 Jun 1977	LV2F S3B S37B-ISS	811 x 869 x 99.2 x 101.7
29, 143		DMSP B5D1-3	01 May 1978	LV2F S3B S37B-ISS	564 x 653 x 97.6 x 96.9
30, 264		DMSP B5D1-4	06 Jun 1979	LV2F S3B S37B-ISS	820 x 838 x 98.8 x 101.1
31, 304		DMSP B5D1-5	14 Jul 1980	LV2F S3B S37B-ISS	Failure: 2nd stage exploded

Notes: All launches from Vandenberg.


 Titan 4

Gunter Krebs (listing)

American launcher

Titan 4 types

Titan 401: always with Centaur-G'

Titan-402: always with IUS

Titan-403: no upper stage, Vandenberg

Titan-404: no upper stage, Vandenberg

Titan-405: no upper stage, Cape Canaveral

The difference between 403 and 404 is the type of payload adapter. One has a system for acomodating shuttle type payloads, but information is conflicting, which one.

Titan 4 launches

#	Launch id	Payload	Launch Date	Site	Type	Status/Comment (orbit in perigee x apogee x inclination x period)
1, K1	89046	DSP F14	14 Jun 1989	C LC41	402 IUS
2, K4	90050	NOSS 12	08 Jun 1990	C LC41	405
3, K6	90095	DSP F15	13 Nov 1990	C LC41	402 IUS
4, K5	91017	Lacrosse 2	08 Mar 1991	V SLC4E	404
5, K8	91076	NOSS 13	08 Nov 1991	V SLC4E	403
6, K3	92083	KH 12-2	28 Nov 1992	V SLC4E	404 TPA
7, K11	n/a	NOSS 14	2 Aug 1993 at 19:59 UT	V SLC4E	403	Failure: exploded after 1 min 41 s
8, K10	94009	USA 099	7 Feb 1994 at 21:47 UT	C LC40	401 Centaur-G' (TC12)
9, K7	94026	USA 103	3 May 1994 at 15:55 UT	C LC41	401 Centaur-G' (TC10)
10, K9	94054	USA 105	27 Aug 1994 at 08:58 UT	C LC41	401 Centaur-G' (TC11)
11, K14	94084	DSP 3-5	22 Dec 1994 at 22:19 UT	C LC40	402 (K14) IUS
12, K23	95022	USA 110	14 May 1995 at 13:45 UT	C LC40	401 (K23) Centaur-G' (TC17)
13, K19	95034	USA 112	10 Jul 1995 at 12:38 UT	C LC41	401 (K19) Centaur-G' (TC8)	The rocket had the large (86 foot) payload shroud
14, K21	95060	USA 115	06 Nov 1995 at 05:15 UT	C LC40	401 (K21) Centaur-G' (TC-13)
15, K15	95066	KH 12-3	05 Dec 1995 at 21:18 UT	V SLC4E	404 (K15)


 Missions

Scientific

Astronomy

Geodesy

Observation of ionosphere

Observation of high atmosphere

Observation of magnetosphere

Observation of meteorites

Observation of the Sun

Observation of the Earth

Meteorology

Geostationary satellites

LEO satellites

Remote sensing satellites

Telecommunications

Geostationary satellites

LEO satellites

Navigation

Navigation satellites

Special topics

Radioactive payload and debris


 Astronomy

Gamma-ray astronomy

1961

(014)	Explorer 11

1964

Cosmos 0051

1968

Cosmos 0208

Cosmos 0251

Cosmos 0264

1972

(090)	Explorer 48

1973

Cosmos 0561

1975

(072)	Cos B

1977

(049)	Signe 3

1979

(082)	Heao 3

1987

(012)	Astro C

1989

(096)	Granat

1990

(058)	Gamma

1991

(027)	GRO

IR astronomy

1983

(004)	Iras

1989

(089)	Cobe

1995

(062)	ISO

Multi-band astronomy

1989

(062)	Hipparcos

1990

(037)	HST

UV astronomy

1964

Cosmos 0051

1966

(031)	OAO 1

1968

(110)	OAO 2

1971

(030)	Tournesol

1972

(014)	TD 1A

(065)	OAO 3

1974

(070)	ANS

1975

(092)	Aura

1977

(012)	IUE

1983

(020)	Astron

1992

(031)	EUVE

1993

(062)	Alexis

1995

(004)	Spartan 201-2

(048)	Spartan 201-3

X-ray astronomy

1968

Cosmos 0208

1970

(107)	Explorer 42

1972

(065)	OAO 3

1974

(070)	ANS

(077)	Ariel 5

1975

(037)	Explorer 53

1977

(075)	Heao 1

1978

(103)	Heao 2

1979

(014)	Corsa B

(047)	Ariel 6

1983

(011)	Astro B

(051)	Exosat

1985

(048)	Spartan 101-1

1987

(012)	Astro C

1989

(096)	Granat

1990

(049)	Rosat

(058)	Gamma

1993

(011)	Astro D

1995

(074)	XTE

Radio astronomy

1968

(055)	Explorer 38

1983

(067)	Prognoz 09

1991

(050)	Sara


 Geodesy

1960

(009)	Echo 1

1962

(060)	Anna 1B

1964

(001)	Secor 01B

(004)	Echo 2

(064)	Explorer 22

1965

(016)	GGSE 2

(016)	GGSE 3

(016)	Secor 03

(017)	Secor 02

(027)	Secor 04

(032)	Explorer 27

(063)	Secor 05

(089)	Explorer 29

1966

(013)	Diapason

(051)	Secor 06

GGTS 1

(056)	Pageos

(077)	Secor 07

(089)	Secor 08

1967

(011)	Diadème 1

(014)	Diadème 2

(053)	GGSE 4

(053)	GGSE 5

(065)	Secor 09

DODGE

1968

(002)	Explorer 36

Cosmos 0203

Cosmos 0256

1969

Cosmos 0272

(037)	Secor 13

Cosmos 0312

1970

TOPO 1

1971

Cosmos 0409

Cosmos 0457

1972

Cosmos 0480

Cosmos 0539

1973

Cosmos 0585

1974

Cosmos 0650

Cosmos 0675

1975

(010)	Starlette

Cosmos 0708

(027)	Geos 3

(039)	Castor

Cosmos 0770

1976

Cosmos 0807

(039)	Lageos 1

Cosmos 842

1977

Cosmos 0911

Cosmos 0963

1979

Cosmos 1067

1980

Cosmos 1312

1981

Cosmos 1410

1982

Cosmos 1510

1984

Cosmos 1589

1985

Cosmos 1660

1986

Cosmos 1732

(061)	Ajisai

Cosmos 1803

1987

Cosmos 1823

1988

Cosmos 1950

1989

Etalon 1

Etalon 2

(068)	Cosmos 2037

1990

Etalon 3

Cosmos 2088

1992

(070)	Lageos 2

1993

(061)	Stella

1994

(078)	GEO-IK

1995

GFZ 1


 Observation of ionosphere

1957

(001)	Sputnik 01

1958

(001)	Explorer 01

(003)	Explorer 03

(004)	Sputnik 03

(005)	Explorer 04

1960

(014)	Explorer 08

1961

(015)	Solrad 03

1962

(008)	Cosmos 0001

Cosmos 0002

Cosmos 0003

(015)	Ariel 1

Cosmos 0007

Cosmos 0008

(049)	Alouette 1

Cosmos 0010

Cosmos 0012

1963

Cosmos 0013

Cosmos 0015

Cosmos 0016

Cosmos 0017

Cosmos 0018

Cosmos 0019

1964

(006)	Elektron 1

(015)	Ariel 2

(038)	Elektron 3

(051)	Explorer 20

(064)	Explorer 22

(076)	Explorer 25

(086)	Explorer 26

1965

(031)	Explorer 27

(054)	Proton 1

(087)	Proton 2

(098)	Explorer 31

(098)	Alouette 2

(101)	FR 1

1966

(060)	Proton 3

1967

(042)	Ariel 3

Cosmos 0163

1968

(041)	Esro 2B

(66)	Explorer 40

(084)	Esro 1A

(103)	Proton 4

Cosmos 0255

1969

(009)	Isis 1

(083)	Esro 1B

(097)	Azur

Intercosmos 02

1970

Cosmos 0321

Intercosmos 03

Cosmos 0381

1971

(024)	Isis 2

(080)	Shinsei

Intercosmos 05

(109)	Ariel 4

(119)	Auréole 1

1972

Cosmos 0477

Cosmos 0484

Intercosmos 06

Cosmos 0490

(064)	Denpa

(092)	Esro 4

Intercosmos 08

(100)	Aeros 1

1973

Intercosmos 09

Intercosmos 10

(107)	Auréole 2

1974

(055)	Aeros 2

(089)	Intasat

1975

(014)	Taiyo

Intercosmos 13

(033)	Aryabhata

Intercosmos 14

1976

(019)	Ume 1

Intercosmos 15

1977

Cosmos 0900

Intercosmos 17

1978

(014)	Exos A

(099)	Intercosmos 18

1979

Intercosmos 19

1981

(070)	Dynamics Explorer 2

(093)	Dong Fang Hong 09

(094)	Auréole 3

1984

Cosmos 1543

1986

(019)	Viking

1989

(016)	Exos D

1994

(014)	Koronas 1

(027)	Sross C2

1995

(002)	Astrid


 Observation of high atmosphere

1958

(002)	Vanguard 1

1959

(001)	Vanguard 2

(009)	Explorer 07

1961

(004)	Explorer 09

1963

(009)	Explorer 17

(053)	Explorer 19

1964

(015)	Ariel 2

Cosmos 0049

(076)	Explorer 24

(084)	San Marco 1

1966

(043)	Explorer 32

1967

(038)	San Marco 2

(042)	Ariel 3

1968

(066)	Explorer 39

Cosmos 0261

Cosmos 0262

1969

(088)	Intercosmos 01

1970

(017)	Dial-Wika

Cosmos 0348

Intercosmos 04

(109)	Péole

1971

(036)	San Marco 3

(071)	Eole

(109)	Ariel 4

1972

Intercosmos 07

1973

(101)	Explorer 51

1974

(009)	San Marco 4

Intercosmos 11

Intercosmos 12

1975

(096)	Explorer 54

(107)	Explorer 55

1979

(013)	AEM 2

(017)	Solwind

1981

(100)	SME

1984

(015)	Exos C

(108)	ERBS

1988

(026)	San Marco 5

1989

Pion 1

Pion 2

Pion 3

Pion 4

1990

(028)	Pegsat

CRRES

1993

(023)	Spartan 201-1

1994

(006)	Bremsat


 Observation of magnetosphere

1959

(004)	Explorer 06

1961

(020)	Explorer 12

1962

(050)	Explorer 14

1963

(046)	Explorer 18

1964

(006)	Elektron 1

(006)	Elektron 2

(038)	Elektron 3

(038)	Elektron 4

Cosmos 0041

(054)	OGO 1

(060)	Explorer 21

1965

(042)	Explorer 28

(081)	OGO 2

1966

(049)	OGO 3

1967

(073)	OGO 4

1968

(014)	OGO 5

(109)	Heos 1

1969

(051)	OGO 6

(053)	Explorer 41

1971

(019)	Explorer 43

(096)	Explorer 45

1972

(005)	Heos 2

(029)	Prognoz 01

(046)	Prognoz 02

(073)	Explorer 47

1973

(009)	Prognoz 03

(078)	Explorer 50

1974

(040)	Explorer 52

1975

Intercosmos 14

(122)	Prognoz 04

1976

(112)	Prognoz 05

1977

Cosmos 0900

(029)	ESA-Geos 1

(093)	Prognoz 06

(102)	ISEE 1

(102)	ISEE 2

1978

(071)	ESA-Geos 2

(079)	ISEE 3

(087)	Exos B

(099)	Intercosmos 18

(101)	Prognoz 07

1980

(103)	Prognoz 08

1981

(070)	Dynamics Explorer 1

(070)	Dynamics Explorer 2

(094)	Auréole 3

1984

(088)	AMPTE CCE

(088)	AMPTE IRM

(088)	AMPTE UKS

1986

(019)	Viking

1989

(016)	Exos D

Aktivny

(080)	Magion 2

1991

(086)	Magion 3

1992

(064)	Freja

1994

(014)	Koronas 1

(046)	Apex

1995

(002)	Astrid

(039)	Prognoz 11

(039)	Magion 4

1996

(013)	Polar


 Observation of meteorites

1961

(022)	Explorer 13

1962

(070)	Explorer 16

1964

(074)	Explorer 23

1965

(009)	Pegasus 1

(039)	Pegasus 2

(060)	Pegasus 3

1972

(061)	Explorer 46

1984

(034)	LDEF


 Observation of the Sun

1957

(002)	Sputnik 02

1959

(007)	Vanguard 3

1962

(006)	OSO 1

1965

(007)	OSO 2

Solrad 08

1967

(020)	OSO 3

Cosmos 166

(100)	OSO 4

1968

(17)	Solrad 09

Cosmos 215

Cosmos 230

1969

(006)	OSO 5

(068)	OSO 6

1970

Cosmos 381

1971

(030)	Tournesol

(058)	Solrad 10

(083)	OSO 7

1972

Cosmos 484

1975

(014)	Taiyo

(057)	OSO 8

(092)	Aura

1976

Intercosmos 16

1978

(079)	ISEE 3

1980

(014)	SMM

1981

(017)	Astro A

1983

(067)	Prognoz 09

1993

(023)	Spartan 201-1

1994

(014)	Koronas 1

(059)	Spartan 204-1

(071)	Wind 1

1995

(065)	Soho


 Meteorological geostationary satellites

1966

(110)	ATS 1

1967

(111)	ATS 3

1974

(033)	SMS 1

1975

(011)	SMS 2

(100)	Goes 1

1977

(048)	Goes 2

(065)	GMS 1

(108)	Meteosat 1

1978

(062)	Goes 3

1980

(074)	Goes 4

1981

(049)	Goes 5

(057)	Meteosat 2

(076)	GMS 2

1982

(031)	Insat 1A

(041)	Goes 6

1983

(089)	Insat 1B

1984

(080)	GMS 3

1987

(022)	Goes 7

1988

Cosmos 1940

(051)	Meteosat 3

(063)	Insat 1C

1989

(020)	Meteosat 4

(070)	GMS 4

1990

(051)	Insat 1D

1991

(015)	Meteosat 5

1992

(041)	Insat 2A

1993

(048)	Insat 2B

(073)	Meteosat 6

1994

(022)	Goes 8

(069)	Electro 1

1995

(011)	GMS 5

(025)	Goes 9


 Meteorological LEO satellites

1959

(009)	Explorer 07

1960

(002)	Tiros 01

(016)	Tiros 02

1961

(017)	Tiros 03

1962

(002)	Tiros 04

(025)	Tiros 05

(047)	Tiros 06

1963

(024)	Tiros 07

(054)	Tiros 08

1964

(052)	Nimbus 1

1965

(004)	Tiros 09

(051)	Tiros 10

DMSP B2-1

1966

(008)	Essa 1

(016)	Essa 2

DMSP B2-2

(040)	Nimbus 2

DMSP B4-1

(057)	Cosmos 0122

(087)	Essa 3

1967

(006)	Essa 4

DMSP B4-2

(018)	Cosmos 0144

(036)	Essa 5

DMSP B4-3

DMSP B4-4

(114)	Essa 6

1968

DMSP B4-5

(069)	Essa 7

DMSP B4-6

(114)	Essa 8

1969

(016)	Essa 9

(029)	Meteor 1-01

(037)	Nimbus 3

DMSP B4-7

(084)	Meteor 1-02

1970

(008)	Itos

DMSP B5A-01

Meteor 1-03

(025)	Nimbus 4

Meteor 1-04

Meteor 1-05

DMSP B5A-02

Meteor 1-06

(106)	NOAA 01

1971

Meteor 1-07

DMSP B5A-03

Meteor 1-08

Meteor 1-09

DMSP B5A-04

Meteor 1-10

1972

DMSP B5B-05

Meteor 1-11

Meteor 1-12

(082)	NOAA 02

Meteor 1-13

DMSP B5C-06

(097)	Nimbus 5

1973

Meteor 1-14

Meteor 1-15

DMSP B5C-07

(086)	NOAA 03

1974

Meteor 1-16

DMSP B5C-08

Meteor 1-17

Meteor 1-18

DMSP B5C-09

Meteor 1-19

(089)	NOAA 04

Meteor 1-20

1975

Meteor 1-21

DMSP B5C-10

(052)	Nimbus 6

Meteor 2-01

Meteor 1-22

Meteor 1-23

1976

DMSP B5C-11

Meteor 1-24

Meteor 1-25

(077)	NOAA 05

DMSP B5D1-1 (AMS 1)

Meteor 1-26

1977

Meteor 2-02

Meteor 1-27

DMSP B5D1-2 (AMS 2)

Meteor 1-28

Meteor 2-03

1978

DMSP B5D1-3 (AMS 3)

(096)	Tiros N

(098)	Nimbus 7

1979

Meteor 1-29

Meteor 2-04

DMSP B5D1-4 (AMS 4)

(057)	NOAA 06

Meteor 2-05

1980

(043)	NOAA B

Meteor 1-30

Meteor 2-06

1981

Meteor 2-07

(059)	NOAA 07

Meteor 1-31

1982

Meteor 2-08

Meteor 2-09

DMSP B5D2-1 (AMS 5)

1983

(022)	NOAA 08

Meteor 2-10

DMSP B5D2-2

1984

Meteor 2-11

(123)	NOAA 09

1985

Meteor 2-12

Meteor 3-01

Meteor 2-13

1986

Meteor 2-14

(073)	NOAA 10

1987

Meteor 2-15

(053)	DMSP B5D2-3

Meteor 2-16

1988

Meteor 2-17

DMSP B5D2-4 (USA 29)

Meteor 3-02

(080)	Dong Fang Hong 24(Feng Yun 1-1)

(089)	NOAA 11

1989

Meteor 2-18

(086)	Meteor 3-03

1990

Meteor 2-19

(081)	Dong Fang Hong 30(Feng Yun 1-2)

Meteor 2-20

DMSP B5D2-5 (USA 68)

1991

Meteor 3-04

(032)	NOAA 12

(056)	Meteor 3-05

DMSP B5D2-6 (USA 73)

1993

Meteor 2-21

1994

(003)	Meteor 3-06

(057)	DMSP B5D2-7

(089)	NOAA 14

1995

(015)	DMSP B5D2-8


 Remote sensing satellites

Chronology

1972

(058)	Landsat 1

1975

(004)	Landsat 2

(070)	Dong Fang Hong 03

(110)	Dong Fang Hong 04

(119)	Dong Fang Hong 05

1976

(087)	Dong Fang Hong 06

(117)	Dong Fang Hong 07

1977

Meteor 1-28

1978

(011)	Dong Fang Hong 08

(026)	Landsat 3

(041)	AEM 1

(064)	Seasat

(098)	Nimbus 7

1979

Meteor 1-29

Cosmos 1076

(051)	Bhaskara 1

Intercosmos 20

1980

Cosmos 1151

Meteor 1-30

1981

Intercosmos 21

Meteor 1-31

(115)	Bhaskara 2

1982

(072)	Landsat 4

(090)	Dong Fang Hong 12

1983

(086)	Dong Fang Hong 13

Cosmos 1484

Cosmos 1500

1984

(021)	Landsat 5

(098)	Dong Fang Hong 16

Cosmos 1602

1985

(096)	Dong Fang Hong 17

Cosmos 1689

1986

(019)	Spot 1

Cosmos 1766

(076)	Dong Fang Hong 19

1987

(018)	Momo 1A

Cosmos 1869

(064)	Cosmos 1870

(067)	Dong Fang Hong 20

(075)	Dong Fang Hong 21

1988

(021)	IRS 1A

(056)	Ocean 1

Cosmos 1939

(067)	Dong Fang Hong 23

1989

(038)	Resurs F01

(047)	Resurs F02

(055)	Resurs F03

(063)	Resurs F04

(073)	Resurs F05

1990

(005)	Spot 2

(013)	Momo 1B

(018)	Ocean 2

(047)	Resurs F06

(060)	Resurs F07

(073)	Resurs F08

(082)	Resurs F09

(089)	Dong Fang Hong 33

1991

Almaz

(035)	Resurs F10

(039)	Ocean 3

(044)	Resurs F11

(050)	ERS 1

(050)	Uosat 5

(052)	Resurs F12

(058)	Resurs F13

(061)	IRS 1B

1992

(007)	JERS 1

(024)	Resurs F14

(033)	Resurs F15

(052)	Topex Poseidon

(056)	Resurs F16

(051)	Dong Fang Hong 35

(064)	Dong Fang Hong 36

1993

(009)	SCD

(033)	Resurs F17

(040)	Resurs F18

(053)	Resurs F19

(061)	Spot 3

(063)	Dong Fang Hong 37

1994

(037)	Dong Fang Hong 40

(066)	Ocean 4

(068)	IRS P2

(074)	Resurs O1-3

1995

(021)	ERS 2

(046)	Sich 1

(050)	Resurs F20

(059)	Radarsat

(072)	IRS 1C

1996

(017)	IRS P3

SAR performances

Satellite	Launch date	Resolution
United States
Seasat	1978	25 m
CIS
Cosmos 1870	1987	15 to 30 m
Almaz 1A	1991	10 to 15 m
Europe
ERS 1	1991	26 m
ERS 2	1995	26 m
Japan
JERS 1	1992	25-30 m


Telecommunications LEO satellites
 LEO Telecommunication satellites

1958

(006)	Score

1960

(009)	Echo 1

(013)	Courier 1B

1961

(???)	Oscar 01

1962

(022)	Oscar 02

(029)	Telstar 1

(068)	Relay 1

1963

(013)	Telstar 2

1964

(003)	Relay 2

(004)	Echo 2

1965

(016)	Oscar 03

(030)	Molniya 1-01

Molniya 1-02

(108)	Oscar 04

1966

Cosmos 103

Molniya 1-03

IDSCP 1-1

IDSCP 1-2

IDSCP 1-3

IDSCP 1-4

IDSCP 1-5

IDSCP 1-6

IDSCP 1-7

Molniya 1-04

1967

IDSCP 2-1

IDSCP 2-2

IDSCP 2-3

IDSCP 2-4

IDSCP 2-5

IDSCP 2-6

IDSCP 2-7

IDSCP 2-8

Cosmos 151

Molniya 1-05

IDSCP 3-1

IDSCP 3-2

IDSCP 3-3

IDSCP 3-4

Molniya 1-06

Molniya 1-07

1968

Molniya 1-08

IDSCP 4-1

IDSCP 4-2

IDSCP 4-3

IDSCP 4-4

IDSCP 4-5

IDSCP 4-6

IDSCP 4-7

IDSCP 4-8

Molniya 1-09

Cosmos 236

Molniya 1-10

1969

Molniya 1-11

Molniya 1-12

Cosmos 292

Cosmos 304

1970

(008)	Oscar 05

Molniya 1-13

Cosmos 332

Cosmos 336

Cosmos 337

Cosmos 338

Cosmos 339

Cosmos 340

Cosmos 341

Cosmos 342

Cosmos 343

Molniya 1-14

Molniya 1-15

Cosmos 371

(086)	Cosmos 372

Molniya 1-16

Molniya 1-17

1971

SDS A

Cosmos 407

Cosmos 411

Cosmos 412

Cosmos 413

Cosmos 414

Cosmos 415

Cosmos 416

Cosmos 417

Cosmos 418

Molniya 1-18

(086)	Cosmos 0444

(086)	Cosmos 0445

(086)	Cosmos 0446

(086)	Cosmos 0447

(086)	Cosmos 0448

(086)	Cosmos 0449

(086)	Cosmos 0450

(086)	Cosmos 0451

(100)	Molniya 2-01

Cosmos 468

Molniya 1-19

1972

Molniya 1-20

Molniya 2-02

(043)	Cosmos 494

(057)	Cosmos 0504

(057)	Cosmos 0505

(057)	Cosmos 0506

(057)	Cosmos 0507

(057)	Cosmos 0508

(057)	Cosmos 0509

(057)	Cosmos 0510

(057)	Cosmos 0511

Molniya 2-03

Molniya 1-21

(082)	Oscar 06

Cosmos 528

Cosmos 529

Cosmos 530

Cosmos 531

Cosmos 532

Cosmos 533

Cosmos 534

Cosmos 535

Molniya 1-22

Molniya 2-04

Cosmos 540

1973

Molniya 1-23

Molniya 2-05

Cosmos 564

Cosmos 565

Cosmos 566

Cosmos 567

Cosmos 568

Cosmos 569

Cosmos 570

Cosmos 571

Molniya 2-06

SDS B

Molniya 1-24

(069)	Cosmos 0588

(069)	Cosmos 0589

(069)	Cosmos 0590

(069)	Cosmos 0591

(069)	Cosmos 0592

(069)	Cosmos 0593

(069)	Cosmos 0594

(069)	Cosmos 0595

Molniya 2-07

Molniya 1-25

Molniya 1-26

Cosmos 614

Cosmos 617

Cosmos 618

Cosmos 619

Cosmos 620

Cosmos 621

Cosmos 622

Cosmos 623

Cosmos 624

Molniya 2-08

1974

Molniya 1-27

(024)	Cosmos 0641

(024)	Cosmos 0642

(024)	Cosmos 0643

(024)	Cosmos 0644

(024)	Cosmos 0645

(024)	Cosmos 0646

(024)	Cosmos 0647

(024)	Cosmos 0648

Molniya 2-09

Molniya 2-10

(072)	Cosmos 0677

(072)	Cosmos 0678

(072)	Cosmos 0679

(072)	Cosmos 0680

(072)	Cosmos 0681

(072)	Cosmos 0682

(072)	Cosmos 0683

(072)	Cosmos 0684

Molniya 1-28

(089)	Oscar 07

Molniya 3-01

Molniya 2-11

1975

Molniya 2-12

(016)	Cosmos 0711

(016)	Cosmos 0712

(016)	Cosmos 0713

(016)	Cosmos 0714

(016)	Cosmos 0715

(016)	Cosmos 0716

(016)	Cosmos 0717

(016)	Cosmos 0718

SDS 1

Molniya 3-02

Molniya 1-29

(045)	Cosmos 0732

(045)	Cosmos 0733

(045)	Cosmos 0734

(045)	Cosmos 0735

(045)	Cosmos 0736

(045)	Cosmos 0737

(045)	Cosmos 0738

(045)	Cosmos 0739

Molniya 1-30

Molniya 2-13

Molniya 1-31

Molniya 2-14

Cosmos 761

Cosmos 762

Cosmos 763

Cosmos 764

Cosmos 765

Cosmos 766

Cosmos 767

Cosmos 768

Cosmos 773

Molniya 3-03

Cosmos 783

Molniya 2-15

Molniya 3-04

1976

Molniya 1-32

Cosmos 791

Cosmos 792

Cosmos 793

Cosmos 794

Cosmos 795

Cosmos 796

Cosmos 797

Cosmos 798

Molniya 1-33

Molniya 1-34

Molniya 3-05

SDS 2

Cosmos 825

Cosmos 826

Cosmos 827

Cosmos 828

Cosmos 829

Cosmos 830

Cosmos 831

Cosmos 832

Cosmos 836

Cosmos 841

Molniya 1-35

SDS 3

Cosmos 858

Molniya 2-16

Cosmos 871

Cosmos 872

Cosmos 873

Cosmos 874

Cosmos 875

Cosmos 876

Cosmos 877

Cosmos 878

Molniya 3-06

1977

Molniya 2-17

Molniya 1-36

Molniya 3-07

Molniya 1-37

Cosmos 923

Cosmos 939

Cosmos 940

Cosmos 941

Cosmos 942

Cosmos 943

Cosmos 944

Cosmos 945

Cosmos 946

Molniya 1-38

Molniya 3-08

Cosmos 968

1978

Cosmos 976

Cosmos 977

Cosmos 978

Cosmos 979

Cosmos 980

Cosmos 981

Cosmos 982

Cosmos 983

Molniya 3-09

Cosmos 990

SDS 4

Molniya 1-39

(026)	Oscar 08

Molniya 1-40

Cosmos 1013

Cosmos 1014

Cosmos 1015

Cosmos 1016

Cosmos 1017

Cosmos 1018

Cosmos 1019

Cosmos 1020

Cosmos 1023

Molniya 1-41

SDS 5

Molniya 1-42

Cosmos 1034

Cosmos 1035

Cosmos 1036

Cosmos 1037

Cosmos 1038

Cosmos 1039

Cosmos 1040

Cosmos 1041

Molniya 3-10

Cosmos 1048

Cosmos 1051

Cosmos 1052

Cosmos 1053

Cosmos 1054

Cosmos 1055

Cosmos 1056

Cosmos 1057

Cosmos 1058

1979

Molniya 3-11

Cosmos 1081

Cosmos 1082

Cosmos 1083

Cosmos 1084

Cosmos 1085

Cosmos 1086

Cosmos 1087

Cosmos 1088

Molniya 1-43

Molniya 3-12

Cosmos 1110

Molniya 1-44

Cosmos 1125

Cosmos 1130

Cosmos 1131

Cosmos 1132

Cosmos 1133

Cosmos 1134

Cosmos 1135

Cosmos 1136

Cosmos 1137

(089)	Cosmos 1140

Molniya 1-45

1980

Molniya 1-46

Cosmos 1156

Cosmos 1157

Cosmos 1158

Cosmos 1159

Cosmos 1160

Cosmos 1161

Cosmos 1162

Cosmos 1163

Cosmos 1175

Molniya 1-47

(056)	Cosmos 1190

Cosmos 1192

Cosmos 1193

Cosmos 1194

Cosmos 1195

Cosmos 1196

Cosmos 1197

Cosmos 1198

Cosmos 1199

Molniya 3-13

Molniya 1-48

SDS 6

Cosmos 1228

Cosmos 1229

Cosmos 1230

Cosmos 1231

Cosmos 1232

Cosmos 1233

Cosmos 1234

Cosmos 1235

1981

Molniya 3-14

Molniya 1-49

Cosmos 1250

Cosmos 1251

Cosmos 1252

Cosmos 1253

Cosmos 1254

Cosmos 1255

Cosmos 1256

Cosmos 1257

Molniya 3-15

SDS 7

Cosmos 1269

Molniya 3-16

Molniya 1-50

Cosmos 1287

Cosmos 1288

Cosmos 1289

Cosmos 1290

Cosmos 1291

Cosmos 1292

Cosmos 1293

Cosmos 1294

Cosmos 1302

Cosmos 1305

(100)	Uosat 1

Molniya 3-17

Cosmos 1320

Cosmos 1321

Cosmos 1322

Cosmos 1323

Cosmos 1324

Cosmos 1325

Cosmos 1326

Cosmos 1327

Molniya 1-51

Molniya 1-52

Cosmos 1331

1982

Molniya 1-53

Molniya 3-18

(037)	Cosmos 1354

Cosmos 1357

Cosmos 1358

Cosmos 1359

Cosmos 1360

Cosmos 1361

Cosmos 1362

Cosmos 1363

Cosmos 1364

Molniya 1-54

Cosmos 1371

Molniya 1-55

Cosmos 1388

Cosmos 1389

Cosmos 1390

Cosmos 1391

Cosmos 1392

Cosmos 1393

Cosmos 1394

Cosmos 1395

Molniya 1-55

Molniya 3-19

Cosmos 1420

1983

Cosmos 1429

Cosmos 1430

Cosmos 1431

Cosmos 1432

Cosmos 1433

Cosmos 1434

Cosmos 1435

Cosmos 1436

Molniya 3-20

Molniya 1-56

Molniya 1-57

Cosmos 1452

(058)	Oscar 10

Cosmos 1473

Cosmos 1474

Cosmos 1475

Cosmos 1476

Cosmos 1477

Cosmos 1478

Cosmos 1479

Cosmos 1480

Molniya 1-58

SDS 8

(079)	Cosmos1486

Molniya 3-21

Cosmos 1503

Molniya 1-59

Molniya 3-22

1984

Cosmos 1522

Cosmos 1523

Cosmos 1524

Cosmos 1525

Cosmos 1526

Cosmos 1527

Cosmos 1528

Cosmos 1529

Cosmos 1538

(021)	Uosat 2

Molniya 1-60

Cosmos 1559

Cosmos 1560

Cosmos 1561

Cosmos 1562

Cosmos 1563

Cosmos 1564

Cosmos 1565

Cosmos 1566

Cosmos 1570

Molniya 1-61

Molniya 1-62

SDS 9

Molniya 1-63

1985

Cosmos 1617

Cosmos 1618

Cosmos 1619

Cosmos 1620

Cosmos 1621

Cosmos 1622

Molniya 3-23

(006)	Cosmos 1624

SDS 10

Cosmos 1635

Cosmos 1636

Cosmos 1637

Cosmos 1638

Cosmos 1639

Cosmos 1640

Cosmos 1641

Cosmos 1642

Molniya 3-24

Molniya 3-25

Molniya 1-64

Cosmos 1680

Molniya 3-26

Molniya 1-65

Molniya 1-66

Molniya 3-27

1986

Cosmos 1616

Cosmos 1617

Cosmos 1618

Cosmos 1619

Cosmos 1620

Cosmos 1621

Cosmos 1622

Cosmos 1623

(030)	Cosmos 1741

Molniya 3-28

Molniya 3-29

Cosmos 1763

Molniya 1-67

Cosmos 1770

(061)	Fuji 1A

Molniya 1-68

Molniya 3-30

Molniya 1-69

Cosmos 1794

Cosmos 1795

Cosmos 1796

Cosmos 1797

Cosmos 1798

Cosmos 1799

Cosmos 1800

Cosmos 1801

Molniya 1-70

1987

Cosmos 1814

Molniya 3-31

SDS 11

Cosmos 1827

Cosmos 1828

Cosmos 1829

Cosmos 1830

Cosmos 1831

Cosmos 1832

(049)	Cosmos 1850

(051)	Cosmos 1852

(051)	Cosmos 1853

(051)	Cosmos 1854

(051)	Cosmos 1855

(051)	Cosmos 1856

(051)	Cosmos 1857

(051)	Cosmos 1858

(051)	Cosmos 1859

Cosmos 1875

Cosmos 1876

Cosmos 1877

Cosmos 1878

Cosmos 1879

Cosmos 1880

Cosmos 1898

1988

Cosmos 1909

Cosmos 1910

Cosmos 1911

Cosmos 1911

Cosmos 1912

Cosmos 1913

Cosmos 1914

(016)	Cosmos 1924

(016)	Cosmos 1925

(016)	Cosmos 1926

(016)	Cosmos 1927

(016)	Cosmos 1928

(016)	Cosmos 1929

(016)	Cosmos 1930

(016)	Cosmos 1931

(017)	Molniya 1-71

(022)	Molniya 1-72

Cosmos 1937

Molniya 3-32

(051)	Oscar 13

Cosmos 1954

Molniya 1-73

Molniya 3-33

SDS 12

(112)	Molniya 3-34

(115)	Molniya 1-74

1989

(005)	Cosmos 1992

(009)	Cosmos 1994

(009)	Cosmos 1995

(009)	Cosmos 1996

(009)	Cosmos 1997

(009)	Cosmos 1998

(009)	Cosmos 1999

Molniya 1-75

(025)	Cosmos 2008

(025)	Cosmos 2009

(025)	Cosmos 2010

(025)	Cosmos 2011

(025)	Cosmos 2012

(025)	Cosmos 2013

(025)	Cosmos 2014

(025)	Cosmos 2015

(043)	Molniya 3-35

(074)	Cosmos 2038

(074)	Cosmos 2039

(074)	Cosmos 2040

(074)	Cosmos 2041

(074)	Cosmos 2042

(074)	Cosmos 2043

Molniya 1-76

(094)	Molniya 3-36

1990

(004)	Cosmos 2056

(005)	Uosat 3

(005)	Uosat 4

(005)	Pacsat

(005)	Dove

(005)	Webersat

(005)	Lusat

(006)	Molniya 3-37

(013)	Fuji 1B

(029)	Cosmos 2064

(029)	Cosmos 2065

(029)	Cosmos 2066

(029)	Cosmos 2067

(029)	Cosmos 2068

(029)	Cosmos 2069

(029)	Cosmos 2070

(029)	Cosmos 2071

Molniya 1-77

Molniya 3-38

Cosmos 2090

Cosmos 2091

Cosmos 2092

Cosmos 2093

Cosmos 2094

Cosmos 2095

Molniya 1-78

Molniya 3-39

Molniya 1-79

(111)	Cosmos 2112

Cosmos 2114

Cosmos 2115

Cosmos 2116

Cosmos 2117

Cosmos 2118

Cosmos 2119

1991

(006)	Informator

Cosmos 2125

Cosmos 2126

Cosmos 2127

Cosmos 2128

Cosmos 2129

Cosmos 2130

Cosmos 2131

Cosmos 2132

Molniya 1-80

Molniya 3-40

Cosmos 2143

Cosmos 2144

Cosmos 2145

Cosmos 2146

Cosmos 2147

Cosmos 2148

Cosmos 2150

Molniya 1-81

(050)	Uosat 5

(050)	Orbcomm X

Molniya 1-82

Molniya 3-41

Cosmos 2157

Cosmos 2158

Cosmos 2159

Cosmos 2160

Cosmos 2161

Cosmos 2162

Cosmos 2165

Cosmos 2166

Cosmos 2167

Cosmos 2168

Cosmos 2169

Cosmos 2170

1992

Molniya 1-83

Cosmos 2187

Cosmos 2188

Cosmos 2189

Cosmos 2190

Cosmos 2191

Cosmos 2192

Cosmos 2193

Cosmos 2194

Cosmos 2197

Cosmos 2198

Cosmos 2199

Cosmos 2200

Cosmos 2201

Cosmos 2202

Molniya 1-84

(052)	Kitsat A

Cosmos 2208

(067)	Molniya 3-42

Cosmos 2211

Cosmos 2212

Cosmos 2213

Cosmos 2214

Cosmos 2215

Cosmos 2216

Molniya 3-43

1993

(002)	Molniya 1-85

(009)	Orbcom XP 1

(025)	Molniya 3-44

(029)	Cosmos 2244

(030)	Cosmos 2245

(030)	Cosmos 2246

(030)	Cosmos 2247

(030)	Cosmos 2248

(030)	Cosmos 2249

(030)	Cosmos 2250

(035)	Molniya 1-86

(036)	Cosmos 2251

(038)	Cosmos 2252

(038)	Cosmos 2253

(038)	Cosmos 2254

(038)	Cosmos 2255

(038)	Cosmos 2256

(038)	Cosmos 2257

(055)	Temisat

(049)	Molniya 3-45

(061)	Eyesat

(061)	Itamsat

(061)	Healthsat

(061)	Kitsat B

(061)	Posat

(079)	Molniya 1-87

1994

(011)	Cosmos 2268

(011)	Cosmos 2269

(011)	Cosmos 2270

(011)	Cosmos 2271

(011)	Cosmos 2272

(011)	Cosmos 2273

(051)	Molniya 3-46

(081)	Molniya 1-88

(085)	RS 15

(083)	Cosmos 2298

(086)	Cosmos 2299

(086)	Cosmos 2300

(086)	Cosmos 2301

(086)	Cosmos 2302

(086)	Cosmos 2303

(086)	Cosmos 2304

1995

(002)	Faisat

(017)	Orbcomm FM 1

(017)	Orbcomm FM 2

(042)	Molniya 3-47

1996

(009)	Gonets-D1 #?

(009)	Gonets-D1 #?

(009)	Gonets-D1 #?

(009)	Cosmos 2328

(009)	Cosmos 2329

(009)	Cosmos 2330


Telecommunications geostationary satellites
 Geostationary telecommunication satellites

See also the Clarke Belt list

1964

(047)	Syncom 3

1965

(028)	Intelsat 101

1966

(110)	ATS 1

1967

(001)	Intelsat 202

(026)	Intelsat 203

(094)	Intelsat 204

(111)	ATS 3

1968

(081)	LES 6

(116)	Intelsat 302

1969

(011)	Intelsat 303

(045)	Intelsat 304

(069)	ATS 5

(101)	Skynet 1A

1970

(003)	Intelsat 306

(021)	Nato 1

(032)	Intelsat 307

(055)	Intelsat 308

1971

(006)	Intelsat 402

(009)	Nato 2

(095)	DSCS 2-01

(095)	DSCS 2-02

(116)	Intelsat 403

1972

(003)	Intelsat 404

(041)	Intelsat 405

(090)	Anik A1

1973

(023)	Anik A2

(058)	Intelsat 407

(100)	DSCS 2-03

(100)	DSCS 2-04

1974

(014)	Cosmos 0637

(022)	Westar 1

(039)	ATS 6

(060)	Molniya 1S

(075)	Westar 2

(093)	Intelsat 408

(094)	Skynet 2B

(101)	Symphonie 1

1975

(038)	Anik A3

(042)	Intelsat 401

(077)	Symphonie 2

(091)	Intelsat 4A01

(117)	Satcom 1

(123)	Raduga 01

1976

(004)	CTS

(010)	Intelsat 4A02

(017)	Marisat 1

(023)	LES 8

(023)	LES 9

(029)	Satcom 2

(035)	Nato 3A

(042)	Comstar 1

(053)	Marisat 2

(066)	Palapa A1

(073)	Comstar 2

(092)	Raduga 02

(101)	Marisat 3

(107)	Ekran 01

1977

(014)	ETS 2

(018)	Palapa A2

(034)	DSCS 2-07

(034)	DSCS 2-08

(041)	Intelsat 4A04

(071)	Raduga 03

(092)	Ekran 02

(118)	Sakura 1

1978

(002)	Intelsat 4A03

(016)	Fleetsatcom 1

(035)	Intelsat 4A06

(039)	Yuri 1

(044)	OTS 2

(068)	Comstar 3

(073)	Raduga 04

(106)	Nato 3C

(113)	DSCS 2-11

(113)	DSCS 2-12

(116)	Anik B1

(118)	Gorizont 01

1979

(015)	Ekran 03

(035)	Raduga 05

(038)	Fleetsatcom 2

(062)	Gorizont 02

(072)	Westar 3

(087)	Ekran 04

(098)	DSCS 2-13

(098)	DSCS 2-14

(105)	Gorizont 03

1980

(004)	Fleetsatcom 3

(016)	Raduga 06

(049)	Gorizont 04

(060)	Ekran 05

(081)	Raduga 07

(087)	Fleetsatcom 4

(091)	SBS 1

(098)	Intelsat 502

(104)	Ekran 06

1981

(018)	Comstar 4

(027)	Raduga 08

(050)	Intelsat 501

(057)	Apple

(061)	Ekran 07

(069)	Raduga 09

(073)	Fleetsatcom 5

(096)	SBS 2

(102)	Raduga 10

(114)	Satcom 3R

(119)	Intelsat 503

(122)	Marecs A

1982

(004)	Satcom 4

(009)	Ekran 08

(014)	Westar 4

(017)	Intelsat 504

(020)	Gorizont 05

(031)	Insat 1A

(044)	Cosmos 1366

(058)	Westar 5

(082)	Anik D1

(093)	Ekran 09

(097)	Intelsat 505

(103)	Gorizont 06

(105)	Aurora 1

(106)	DSCS 2-15

(106)	DSCS 3-01

(110)	SBS 3

(110)	Anik C3

(113)	Raduga 11

1983

(006)	Sakura 2A

(016)	Ekran 10

(026)	TDRS 1

(028)	Raduga 12

(030)	Satcom 1R

(047)	Intelsat 506

(058)	Eutelsat 1F1

(059)	Anik C2

(059)	Palapa B1

(065)	Galaxy 1

(066)	Gorizont 07

(077)	Telstar 301

(081)	Sakura 2B

(088)	Raduga 13

(089)	Insat 1B

(094)	Satcom 2R

(098)	Galaxy 2

(100)	Ekran 11

(105)	Intelsat 507

(118)	Gorizont 08

1984

(005)	Yuri 2A

(016)	Raduga 14

(022)	Cosmos 1540

(023)	Intelsat 508

(028)	Ekran 12

(035)	Dong Fang Hong 15

(041)	Gorizont 09

(049)	Spacenet 1

(063)	Raduga 15

(078)	Gorizont 10

(081)	Eutelsat 1F2

(081)	Telecom 1A

(090)	Ekran 13

(093)	SBS 4

(093)	Leasat 2

(093)	Telstar 302

(101)	Galaxy 3

(113)	Anik D2

(113)	Leasat 1

(114)	Spacenet 2

(114)	Marecs B2

(115)	Nato 3D

1985

(007)	Gorizont 11

(015)	Arabsat 1A

(015)	Brazilsat A1

(024)	Ekran 14

(025)	Intelsat 510

(028)	Anik C1

(028)	Leasat 3

(035)	Gstar 1

(035)	Telecom 1B

(048)	Morelos 1

(048)	Arabsat 1B

(048)	Telstar 303

(055)	Intelsat 511

(070)	Raduga 16

(076)	Optus A1

(076)	ASC 1

(076)	Leasat 4

(087)	Intelsat 512

(092)	DSCS 3-02

(092)	DSCS 3-03

(102)	Cosmos 1700

(107)	Raduga 17

(109)	Morelos 2

(109)	Optus A2

(109)	Satcom K2

1986

(003)	Satcom K1

(007)	Raduga 18

(010)	Dong Fang Hong 18

(016)	Yuri 2B

(026)	Gstar 2

(026)	Brazilsat A2

(027)	Cosmos 1738

(038)	Ekran 15

(044)	Gorizont 12

(082)	Raduga 19

(090)	Gorizont 13

(096)	Fleetsatcom 7

1987

(028)	Raduga 20

(029)	Palapa B2P

(040)	Gorizont 14

(070)	ETS 5

(073)	Ekran 16

(078)	Optus A3

(078)	Eutelsat 1F4

(084)	Cosmos 1888

(096)	Cosmos 1897

(100)	Raduga 21

(109)	Ekran 17

1988

(012)	Sakura 3A

(014)	Dong Fang Hong 22

(018)	Spacenet 3R

(018)	Telecom 1C

(028)	Gorizont 15

(036)	Ekran 18

(040)	Intelsat 513

(051)	Panamsat 1

(063)	Insat 1C

(063)	Eutelsat 1F5

(066)	Cosmos 1961

(071)	Gorizont 16

(081)	Gstar 3

(081)	SBS 5

(086)	Sakura 3B

(091)	TDRS 3

(095)	Raduga 22

(098)	TDF 1

(108)	Ekran 19

(109)	Skynet 4B

(109)	Astra 1A

(111)	Dong Fang Hong 25

1989

(004)	Gorizont 17

(006)	Intelsat 515

(020)	Jcsat 1

(021)	TDRS 4

(027)	TELE X

(030)	Raduga 23

(041)	Superbird A1

(041)	DFS 1

(048)	Raduga 1-1

(052)	Gorizont 18

(053)	Olympus

(062)	Tvsat 2

(067)	BSB 1

(069)	DSCS 2-16

(069)	DSCS 3-04

(077)	Fleetsatcom 8

(081)	Gorizont 19

(087)	Intelsat 602

(098)	Raduga 24

(101)	Cosmos 2054

1990

(001)	Skynet 4A

(001)	Jcsat 2

(002)	Leasat 5

(011)	Dong Fang Hong 26

(016)	Raduga 25

(021)	Intelsat 603

(030)	Asiasat 1

(034)	Palapa B2R

(051)	Insat 1D

(054)	Gorizont 20

(056)	Intelsat 604

(061)	Cosmos 2085

(063)	TDF 2

(063)	DFS 2

(074)	BSB 2

(077)	Yuri 3A

(079)	Skynet 4C

(079)	Eutelsat 2F1

(091)	SBS 6

(091)	Galaxy 6

(093)	Inmarsat 2F1

(094)	Gorizont 21

(100)	Satcom C1

(100)	Gstar 4

(102)	Gorizont 22

(112)	Raduga 26

(116)	Raduga 1-2

1991

(001)	Nato 4A

(003)	Italsat 1

(003)	Eutelsat 2F2

(014)	Raduga 27

(015)	Astra 1B

(018)	Inmarsat 2F2

(026)	Anik E2

(028)	ASC 2

(037)	Aurora 2

(046)	Gorizont 23

(054)	TDRS 5

(055)	Intelsat 605

(060)	Yuri 3B

(067)	Anik E1

(074)	Gorizont 24

(075)	Intelsat 601

(079)	Cosmos 2172

(083)	Eutelsat 2F3

(084)	Telecom 2A

(084)	Inmarsat 2F3

(087)	Raduga 28

1992

(006)	DSCS 3-05

(010)	Superbird B1

(010)	Arabsat 1C

(013)	Galaxy 5

(017)	Gorizont 25

(021)	Telecom 2B

(021)	Inmarsat 2F4

(027)	Palapa B4

(032)	Intelsat K

(037)	DSCS 3-06

(041)	Insat 2A

(041)	Eutelsat 2F4

(043)	Gorizont 26

(054)	Optus B1

(057)	Satcom C4

(060)	Hispasat 1A

(060)	Satcom C3

(066)	DFS 3

(072)	Galaxy 7

(074)	Ekran 20

(082)	Gorizont 27

(084)	Superbird A2

1993

(003)	TDRS 6

(029)	Raduga 29

(015)	UHF 1

(031)	Astra 1C

(039)	Galaxy 4

(046)	DSCS 3-07

(048)	Hispasat 1B

(048)	Insat 2B

(056)	UHF 2

(058)	ACTS

(062)	Raduga 30

(066)	Intelsat 701

(069)	Gorizont 28

(072)	Gorizont 29

(074)	DSCS 3-08

(076)	Nato 4B

(077)	Telstar 401

(078)	DBS 1

(078)	Thaicom 1

1994

(002)	Gals 1

(008)	Raduga 1-3

(009)	USA 099

(012)	Raduga 31

(013)	Galaxy 1R

(030)	Gorizont 30

(034)	Intelsat 702

(035)	UHF 3

(040)	Panamsat 2

(040)	Yuri 3N

(043)	Apstar 1

(047)	DBS 2

(049)	Brazilsat B1

(049)	Turksat 1B

(055)	Optus B3

(060)	Cosmos 2291

(064)	Intelsat 703

(065)	Solidaridad 2

(065)	Thaicom 2

(067)	Express 01

(070)	Astra 1D

(079)	Orion 1

(080)	Dong Fang Hong 41

(082)	Luch 0

(087)	Raduga 32

1995

(001)	Intelsat 704

(003)	UHF 4

(013)	Intelsat 705

(016)	Brazilsat B2

(016)	Hotbird 1

(019)	AMSC 1

(023)	Intelsat 706

(027)	UHF 5

(029)	DBS 3

(035)	TDRS 7

(038)	DSCS 3-09

(040)	Panamsat 4

(041)	Koreasat 1

(043)	Jcsat 3

(044)	N Star A

(045)	Cosmos 2319

(049)	Telstar 402R

(054)	Luch 1

(055)	Astra 1E

(057)	UHF 6

(060)	USA 115

(063)	Gals 2

(067)	Telecom 2C

(067)	Insat 2C

(069)	Galaxy 3R

(073)	Echostar 1

1996

(002)	Panamsat 3R

(002)	Measat 1

(003)	Koreasat 2

(005)	Gorizont 31

(006)	Palapa C1

(007)	N Star B

(015)	Intelsat 707


 Navigation satellites

1960

Transit 1B

(007)	Transit 2A

1961

Transit 3B (loft 1)

(015)	Transit 4A

(031)	Transit 4B

1962

Transit 5A

1963

Transit 7 (5A3)

(038)	Transit 5BN1

(049)	Transit 5BN2

1964

Transit 9 (5C 1)

Transit 5B 4

Transit 5B 5

1965

NNSS 30 030 (Transit 5B 6)

NNSS 30 040 (Transit 5B 7)

NNSS 30 050 (Transit 10)

1966

NNSS 30 060 (Transit 11)

NNSS 30 070 (Transit 12)

NNSS 30 080 (Transit 13)

NNSS 30 090 (Transit 14)

1967

NNSS 30 120 (Transit 15)

NNSS 30 130 (Transit 16)

Timation 1

NNSS 30 140 (Transit 17)

Cosmos 192

1968

NNSS 30 180 (Transit 18)

Cosmos 220

1969

Cosmos 292

Timation 2 (+ 6 ss sat)

Cosmos 304

1970

Cosmos 332

NNSS 30 190

Cosmos 371

Cosmos 381

Cosmos 385

1971

Cosmos 422

Cosmos 465

1972

Cosmos 475

Cosmos 489

Cosmos 514

Triad 1

1973

Cosmos 574

Cosmos 586

NNSS 30 200

Cosmos 627

1974

Cosmos 628

Cosmos 660

Cosmos 663

Timation 3 (NTS 1)

Cosmos 689

Cosmos 700 (Parus)

1975

Cosmos 726 (Parus)

Cosmos 729

Cosmos 755 (Parus)

Triad 2 (TIP 2)

Cosmos 778 (Parus)

1976

Cosmos 789 (Parus)

Cosmos 800

Cosmos 807

Cosmos 823

Cosmos 842

Cosmos 846

Triad 3 (TIP 3)

Cosmos 864 (Parus)

Cosmos 883 (Tsikada)

Cosmos 887 (Parus)

1977

Cosmos 890

Cosmos 894 (Parus)

Cosmos 911

Cosmos 926 (Tsikada)

Cosmos 928 (Parus)

Cosmos 951 (Parus)

NNSS 30 110

Cosmos 962

Cosmos 971 (Parus)

1978

Cosmos 985 (Parus)

(020)	GPS BI-01

Cosmos 991 (Parus)

Cosmos 994

Cosmos 996 (Parus)

(034)	Cosmos 1000 (Tsikada)

(047)	GPS BI-02

Cosmos 1011 (Parus)

Cosmos 1027

(093)	GPS BI-03

(112)	GPS BI-04

Cosmos 1064

1979

Cosmos 1072 (Parus)

Cosmos 1089 (Parus)

Cosmos 1091 (Parus)

Cosmos 1092 (Tsikada)

Cosmos 1104 (Parus)

Cosmos 1141 (Parus)

1980

Cosmos 1150 (Parus)

Cosmos 1153 (Parus)

(011)	GPS BI-05

Cosmos 1168 (Tsikada)

(032)	GPS BI-06

Cosmos 1181 (Parus)

Cosmos 1225 (Parus)

Cosmos 1226 (Tsikada)

1981

Cosmos 1244 (Parus)

(044)	Nova 1

Cosmos 1275 (Parus)

Cosmos 1295 (Parus)

Cosmos 1304 (Tsikada)

Cosmos 1308 (Parus)

1982

Cosmos 1333 (Parus)

Cosmos 1339 (Tsikada)

Cosmos 1344 (Parus)

Cosmos 1349 (Parus)

Cosmos 1380

Cosmos 1383 (Tsikada)

Cosmos 1386 (Parus)

Cosmos 1413 (dummy)

Cosmos 1414 (Glonass)

Cosmos 1415 (dummy)

Cosmos 1417 (Parus)

1983

Cosmos 1428 (Parus)

Cosmos 1447 (Tsikada)

Cosmos 1448 (Parus)

Cosmos 1459 (Parus)

Cosmos 1464 (Parus)

(072)	GPS BI-08

Cosmos 1490 (Glonass)

Cosmos 1491 (Glonass)

Cosmos 1492 (dummy)

Cosmos 1506 (Tsikada)

Cosmos 1513 (Parus)

Cosmos 1519 (Glonass)

Cosmos 1520 (Glonass)

Cosmos 1521 (dummy)

1984

Cosmos 1531 (Parus)

Cosmos 1535 (Parus)

Cosmos 1550 (Parus)

Cosmos 1553 (Tsikada)

Cosmos 1554 (Glonass)

Cosmos 1555 (Glonass)

Cosmos 1556 (dummy)

(059)	GPS BI-09

Cosmos 1574 (Tsikada)

Cosmos 1577

Cosmos 1593 (Glonass)

Cosmos 1594 (dummy)

Cosmos 1595 (Glonass)

(097)	GPS BI-10

Cosmos 1598 (Parus)

Cosmos 1605 (Parus)

(110)	Nova 2

Cosmos 1610 (Parus)

1985

Cosmos 1627 (Parus)

Cosmos 1634 (Parus)

Cosmos 1650 (Glonass)

Cosmos 1651 (Glonass)

Cosmos 1652 (dummy)

Cosmos 1655 (Tsikada)

(095)	GPS BI-11

SOOS ? Transit 19 (SOOS 240 - 300)

SOOS ?Transit 20

Cosmos 1704 (Parus)

Cosmos 1709 (Parus)

Cosmos 1710 (Glonass)

Cosmos 1711 (Glonass)

Cosmos 1712 (dummy)

1986

Cosmos 1725 (Parus)

Cosmos 1727 (Tsikada)

Cosmos 1745 (Parus)

Cosmos 1759 (Parus)

Cosmos 1778 (Glonass)

Cosmos 1779 (Glonass)

Cosmos 1780 (Glonass)

Cosmos 1791 (Tsikada)

Polar Bear (17070)

Cosmos 1802 (Parus)

Cosmos 1808 (Parus)

1987

Cosmos 1816 (Tsikada)

Cosmos 1821 (Parus)

Cosmos 1838 (Glonass)

Cosmos 1839 (Glonass)

Cosmos 1840 (Glonass)

(054)	Cosmos 1861 (Tsikada)

Cosmos 1864 (Parus)

Cosmos 1883 (Glonass)

Cosmos 1884 (Glonass)

Cosmos 1885 (Glonass)

SOOS 270 (Oscar 27)

SOOS 290 (Oscar 29)

Cosmos 1891 (Parus)

Cosmos 1904 (Parus)

1988

Cosmos 1917 (Glonass)

Cosmos 1918 (Glonass)

Cosmos 1919 (Glonass)

(023)	Cosmos 1934 (Parus)

SOOS 230 (Oscar 23)

SOOS 320 (Oscar 32)

Cosmos 1946 (Glonass)

Cosmos 1947 (Glonass)

Cosmos 1948 (Glonass)

(052)	Nova 3

(062)	Cosmos 1959 (Parus)

SOOS 250 (Oscar 25)

SOOS 310 (Oscar 31)

(085)	Cosmos 1970 (Glonass)

(085)	Cosmos 1971 (Glonass)

(085)	Cosmos 1972 (Glonass)

1989

(001)	Cosmos 1987 (Glonass)

(001)	Cosmos 1988 (Glonass)

(001)	Cosmos 1989

(013)	GPS BII-01

(017)	Cosmos 2004 (Parus)

(028)	Cosmos 2016 (Parus)

(031)	Cosmos 2018

(039)	Cosmos 2022 (Glonass)

(039)	Cosmos 2023 (Glonass)

(039)	Cosmos 2024 (Glonass)

(042)	Cosmos 2026 (Parus)

(044)	GPS BII-02

(050)	Nadezhda 1

(059)	Cosmos 2034 (Parus)

(064)	GPS BII-03

(085)	GPS BII-04

(097)	GPS BII-05

1990

(008)	GPS BII-06

(017)	Nadezhda 2

(023)	Cosmos 2061 (Parus)

(025)	GPS BII-07

(036)	Cosmos 2074 (Parus)

(045)	Cosmos 2079 (Glonass)

(045)	Cosmos 2080 (Glonass)

(045)	Cosmos 2081 (Glonass)

(068)	GPS BII-08

Cosmos 2100 (Parus)

(088)	GPS BII-09

(103)	GPS BIIA-10

(110)	Cosmos 2109 (Glonass)

(110)	Cosmos 2110 (Glonass)

(110)	Cosmos 2111 (Glonass)

1991

(007)	Cosmos 2123 (Tsikada)

Cosmos 2135 (Parus)

(019)	Nadezhda 3

(025)	Cosmos 2139 (Glonass)

(025)	Cosmos 2140 (Glonass)

(025)	Cosmos 2141 (Glonass)

Cosmos 2142 (Parus)

(047)	GPS BIIA-11

Cosmos 2154 (Parus)

(081)	Cosmos 2173 (Parus)

1992

(005)	Cosmos 2177 (Glonass)

(005)	Cosmos 2178 (Glonass)

(005)	Cosmos 2179 (Glonass)

Cosmos 2180 (Parus)

Cosmos 2181 (Tsikada)

(009)	GPS BIIA-12

(019)	GPS BIIA-13

Cosmos 2184 (Parus)

Cosmos 2195

(039)	GPS BIIA-14

(047)	Cosmos 2204 (Glonass)

(047)	Cosmos 2205 (Glonass)

(047)	Cosmos 2206 (Glonass)

(058)	GPS BIIA-15

(073)	Cosmos 2218 (Parus)

(079)	GPS BIIA-16

(089)	GPS BIIA-17

1993

(001)	Cosmos 2230 (Tsikada)

(007)	GPS BIIA-18

(008)	Cosmos 2233 (Parus)

(010)	Cosmos 2234 (Glonass)

(010)	Cosmos 2235 (Glonass)

(010)	Cosmos 2236 (Glonass)

(017)	GPS BIIA-19

(020)	Cosmos 2239 (Parus)

(032)	GPS BIIA-20

(042)	GPS BIIA-21

(054)	GPS BIIA-22

(068)	GPS BIIA-23

(070)	Cosmos 2266 (Parus)

1994

(016)	GPS BIIA-24

(021)	Cosmos 2275 (Glonass)

(021)	Cosmos 2276 (Glonass)

(021)	Cosmos 2277 (Glonass)

(024)	Cosmos 2279 (Parus)

(041)	Nadezhda 4

(050)	Cosmos 2287 (Glonass)

(050)	Cosmos 2288 (Glonass)

(050)	Cosmos 2289 (Glonass)

(076)	Cosmos 2294 (Glonass)

(076)	Cosmos 2295 (Glonass)

(076)	Cosmos 2296 (Glonass)

1995

(009)	Cosmos 2307 (Glonass)

(009)	Cosmos 2308 (Glonass)

(009)	Cosmos 2309 (Glonass)

(012)	Cosmos 2310 (Parus)

(032)	Cosmos 2315 (Kurs)

(037)	Cosmos 2316 (Glonass)

(037)	Cosmos 2317 (Glonass)

(037)	Cosmos 2318 (Glonass)

(052)	Cosmos 2321 (Parus)

(068)	Cosmos 2323 (Glonass)

(068)	Cosmos 2324 (Glonass)

(068)	Cosmos 2325 (Glonass)

1996

(004)	Cosmos 2327 (Parus)

(019)	GPS BIIA-25


 Radioactive payload and debris

Radioactive payloads have been a concern for the community ever since radioactive debris decayed on Earth and contaminated entire regions. The first such event was in Jan 1978 when Cosmos 0954 decayed. Since then radioactive debris are closely monitored.

Those nuclear reactors which are to remain in orbit for a hundred years or so also caused problems to scientists. "Nuclear noise" as it is called cause gamma ray disturbances to astronomers. Indeed those reactors interfere periodically with gamma-ray surveys.

Russian satellites

The Russian Rorsat program is the most important program with nuclear reactor equipped satellites (32 spacecrafts). This engine (which name is unknow) contains 50 kg of uranium and provides about 2000 W.

Two other Russian satellites are known to have a Topaz reactor: Cosmos 1818 (87011A) and Cosmos 1867 (87060A). This reactor provides around 5-6 kW power.

US satellites

The United States also used nuclear power on space missions. Two types of engines were used:

- Nuclear reactors which produce energy by nuclear fission (space based reactors use Uranium-235).

- RTGs (Radioisotope Thermoelectric Generator) which use the energy of radioactive decay (current SNAPs use Plutonium-238).

The SNAP (Systems for Nuclear Auxiliary Power) series include:

RTG engines	Nuclear reactors	Uncertain
Transit 4A	OPS 4682 also called SNAPSHOT (65027A)	LES 5
Transit 4B		LES 6
Nimbus 3		OPS 0757 also called Tacsat (69013A)
LES 8
LES 9

Other missions required nuclear power such as the Apollo moon missions experiments, the Viking Mars Landers, Pioneer and Voyager missions and the Galileo probe:

LAUNR	Spacecraft	Orbit
69-099	APOLLO 12	Moon
71-008	APOLLO 14	Moon
71-063	APOLLO 15	Moon
72-012A	PIONEER 10	escaped solar system
72-031	APOLLO 16	Moon
72-096	APOLLO 17	Moon
73-019A	PIONEER 11	escaped solar system
75-075	VIKING 1 LANDER	Mars
75-083	VIKING 2 LANDER	Mars
77-076A	VOYAGER 2	escaped solar system
77-084A	VOYAGER 1	escaped solar system
89-084B	GALILEO	heliocentric orbit (Sun)

Finally 3 missions failed:

Transit 5BN3 on 21 Apr 1964 aboard Thor Ablestar

Nimbus 3A

Apollo 13 (70029A) on 11 Apr 1970 which decayed on 17 Apr 1970